ML12009A118

License Amendment Request Pursuant to 10 CFR 50.90: Use of Modified Alloy 718 Material in Jet Pump Holddown Beams

ML12009A118
Person / Time
Site:	Nine Mile Point
Issue date:	12/30/2011
From:	Payne F Constellation Energy Group, EDF Development, Nine Mile Point
To:	Office of Nuclear Reactor Regulation, Document Control Desk
References
Download: ML12009A118 (107)

Text

This letter forwards proprietary information in accordance with 10 CFR 2.390. The balance of this letter may be considered non-proprietary upon removal of Enclosure 6.

P.O. Box 63 Lycoming, New York 13093 315.349.5206 315.349.1321 Fax CENG a joint venture of C*flteIation 'eDF NINE MILE POINT NUCLEAR STATION December 30, 2011 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 ATTENTION: Document Control Desk

SUBJECT:

Nine Mile Point Nuclear Station Unit No. 2, Docket No. 50-410 License Amendment Request Pursuant to 10 CFR 50.90: Use of Modified Alloy 718 Material in Jet Pump Holddown Beams Pursuant to 10 CFR 50.90, Nine Mile Point Nuclear Station, LLC (NMPNS) hereby requests an amendment to the Nine Mile Point Unit 2 (NMP2) Renewed Facility Operating License NPF-69.

NMPNS is requesting NRC approval to use Modified Alloy 718 material for fabrication of the NMP2 reactor recirculation system jet pump holddown beams. The existing holddown beam material is Alloy X-750. The Modified Alloy 718 material has been included in American Society of Mechanical Engineers (ASME) Code Case N-60-6, "Material for Core Support Structures,Section III, Division 1;" however, this Code Case revision has not yet been approved for use by the NRC in Regulatory Guide 1.84, "Design, Fabrication, and Material Code Case Acceptability, ASME Section III."

NRC approval of this proposed change to the NMP2 current licensing basis would be reflected in a revision to Section 4.5 of the NMP2 Updated Safety Analysis Report (USAR), which provides a description of the materials used in the reactor internals, including the jet pump assemblies. The Technical Specifications are not affected by this amendment request. provides a description and technical bases for the proposed amendment, and existing USAR pages marked up to show the proposed changes. NMPNS has concluded that the activities associated with the proposed amendment represent no significant hazards consideration under the standards set forth This letter forwards proprietary information in accordance with 10 CFR 2.390. The balance of this letter may be considered non-proprietary upon removal of Enclosure 6.

Document Control Desk December 30, 2011 Page 2 in 10 CFR 50.92. A related regulatory commitment regarding Modified Alloy 718 jet pump holddown beam inspection intervals is described in Enclosure 2. provides Toshiba Corporation Record 10-1516, "Code Case Revision," which contains information supporting the requested addition of Modified Alloy 718 material to Code Case N-60-5. (proprietary) provides Toshiba Corporation document SMV-2011-000034-P, Revision 0, "Toshiba Engineering Report, Jet Pump Beam Fabrication - Comparison of Modified Alloy 718 and Alloy X-750 Materials." This document is used to support the evaluation of the proposed change included in Enclosure 1. Enclosure 6 is considered by Toshiba to contain proprietary information exempt from disclosure pursuant to 10 CFR 2.390. Therefore, on behalf of Toshiba, NMPNS hereby makes application to withhold this attachment from public disclosure in accordance with 10 CFR 2.390(b)(1).

The affidavit from Toshiba detailing the reasons for the request to withhold the proprietary information is provided in Enclosure 5. Enclosure 4 provides a non-proprietary version of the same document.

Approval of the proposed license amendment is requested by April 1, 2012, with implementation within 30 days of receipt of the approved amendment. Approval by the requested date is desired to support jet pump modifications scheduled for implementation during the upcoming NMP2 refueling outage, which is currently scheduled to begin in April 2012.

Pursuant to 10 CFR 50.91(b)(1), NMPNS has provided a copy of this license amendment request, with non-proprietary Enclosures, to the appropriate state representative.

Should you have any questions regarding the information in this submittal, please contact John J. Dosa, Director Licensing, at (315) 349-5219.

Manager Operations

Document Control Desk December 30, 2011 Page 3 STATE OF NEW YORK TO WIT:

COUNTY OF OSWEGO I, Frank R. Payne, being duly sworn, state that I am Manager Operations, and that I am duly authorized to execute and file this license amendment request on behalf of Nine Mile Point Nuclear Station, LLC. To the best of my knowledge and belief, the statements contained in this document are true and correct. To the extent that these statements are not based on my personal knowledge, they are based upon information provided by other Nine Mile Point employees and/or consultants. Such information has been reviewed in accordance with company practice and I believe it to be reliable Subscribed and sworn before me, a Notary Public in and for the State of New York and County of

_ (V' ) this 50 day of _[Ce*ei:*;- .2011.

WITNESS my Hand and Notarial Seal: /(. /

Notary Public My Commission Expires:

9//2/20J3 Usa M. Doran Date Notary Public In the State of New York Oswego County Reg. No. 01 D06029220 FRP/DEV My Commission Expires 9/12/2013

Enclosures:

1. Evaluation of the Proposed Change

2. List of Regulatory Commitments

3. Toshiba Corporation Record 10-1516, Code Case Revision

4. SMV-2011-000034-NP, Revision 0, Toshiba Engineering Report, Jet Pump Beam Fabrication -

Comparison of Modified Alloy 718 and Alloy X-750 Materials (Non-Proprietary)

5. Affidavit from Toshiba Corporation Justifying Withholding Proprietary Information

6. SMV-2011-000034-P, Revision 0, Toshiba Engineering Report, Jet Pump Beam Fabrication -

Comparison of Modified Alloy 718 and Alloy X-750 Materials (Proprietary) cc: Regional Administrator, Region I, NRC Project Manager, NRC Resident Inspector, NRC A. L. Peterson, NYSERDA (w/o Enclosure 6)

ENCLOSURE 1 EVALUATION OF THE PROPOSED CHANGE TABLE OF CONTENTS 1.0

SUMMARY

DESCRIPTION 2.0 DETAILED DESCRIPTION 2.1 Description of the Proposed Change 2.2 Background

4.0 REGULATORY EVALUATION

4.1 Applicable Regulatory Requirements/Criteria 4.2 Significant Hazards Consideration 4.3 Conclusions

6.0 REFERENCES

ATTACHMENT

1. Proposed Changes to the Nine Mile Point Unit 2 Updated Safety Analysis Report (USAR) (Mark-up)

Nine Mile Point Nuclear Station, LLC December 30, 2011

ENCLOSURE 1 EVALUATION OF THE PROPOSED CHANGE 1.0

SUMMARY

DESCRIPTION This evaluation supports a request to amend Renewed Facility Operating License NPF-69 for Nine Mile Point Unit 2 (NMP2).

Nine Mile Point Nuclear Station, LLC (NMPNS) is requesting NRC approval to use Modified Alloy 718 material for fabrication of the NMP2 reactor recirculation system jet pump holddown beams. The existing holddown beam material is Alloy X-750. The Modified Alloy 718 material is the same material described by Specification SB-637 and identified as Grade 718 Type 2 in American Society of Mechanical Engineers (ASME) Code Case N-60-6. It has the same chemical composition as conventional Grade 718 (Type 1) material, but the heat treatment condition differs (the reason for using the term "Modified"). For simplicity, the term "Modified Alloy 718" will be used hereafter to identify this material.

The jet pump assemblies are reactor vessel internals but are not core support structures. As noted in Section 4.5.2 of the NMP2 Updated Safety Analysis Report (USAR), such reactor internals are not ASME code components but are fabricated from American Society for Testing and Materials (ASTM) or ASME specification materials. This is consistent with the acceptance criteria in NUREG-0800, Standard Review Plan (SRP), Section 4.5.2, which states that for core support structures and reactor internals, the permitted material specifications are those given in the ASME Code Section III, Division 1, with properties of these materials specified in the ASME Code Section II. In addition, the SRP states that additional permitted materials are identified in ASME Code Cases approved for use by an NRC regulatory guide. The Modified Alloy 718 material has been included in ASME Code Case N-60-6, "Material for Core Support Structures,Section III, Division 1" (see Attachment 2 to Enclosures 4 and 6).

This Code Case revision was approved by ASME on December 6, 2011; however, it has not yet been approved for use by the NRC in a regulatory guide (i.e., Regulatory Guide 1.84). Thus, this license amendment request seeks NRC approval to consider Modified Alloy 718 a permitted reactor internals material for the NMP2 jet pump holddown beams.

2.0 DETAILED DESCRIPTION 2.1 Description of the Proposed Change The proposed change to the NMP2 licensing basis would revise USAR Section 4.5 as shown in . The USAR revision would identify Modified Alloy 718 as the material used to fabricate the jet pump holddown beams. The jet pump inlet mixer pin and insert are made of Alloy X-750 and are not being changed to the Modified Alloy 718 material. Following NRC approval of the license amendment request, the NMP2 USAR will be updated to incorporate the changes identified in in accordance with 10 CFR 50.71(e).

2.2 Background The NMP2 reactor recirculation system includes 20 jet pump assemblies that are located within the reactor pressure vessel (RPV), in the downcomer annulus between the core shroud and the RPV wall.

During normal operation, the jet pumps direct reactor coolant flow to the core. Following a loss of coolant accident, the jet pumps function to maintain the ability to reflood the reactor to two-thirds core height. The jet pump nozzle entry section is connected to the inlet riser by a metal-to-metal, spherical-to-conical seal joint. Firm contact is maintained by a holddown beam (clamp). The holddown beams are currently fabricated from Alloy X-750 material.

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ENCLOSURE 1 EVALUATION OF THE PROPOSED CHANGE NMP2 is planning to replace all 20 of the jet pump inlet mixers in the upcoming Spring 2012 refueling outage. As part of that modification, replacement holddown beams are being provided that are fabricated from Modified Alloy 718 material. NMPNS evaluation of the Modified Alloy 718 material concluded that it has similar or improved material properties and improved resistance to stress corrosion cracking (SCC) initiation and propagation as compared to the existing Alloy X-750 material. Further discussion is provided in the following Technical Evaluation section.

3.0 TECHNICAL EVALUATION

The jet pump holddown beams apply a downward clamping force on each inlet subassembly to resist the elbow and nozzle hydraulic reaction forces. To accommodate the clamping loads generated by holding the inlet-throat subassembly in place, the current holddown beams are fabricated from high strength Alloy X-750 material. As an alternative to the Alloy X-750 material, NMPNS is proposing to use Modified Alloy 718 material, which has been developed based on conventional Alloy 718 material. The Modified Alloy 718 material has similar or improved material properties and improved resistance to SCC initiation and propagation as compared to Alloy X-750 material.

Information that supported the addition of Modified Alloy 718 material to Code Case N-60-5 is provided in Enclosure 3. This information includes data on yield strength, tensile strength, stress intensity, fatigue, and other material properties. The data and evaluations documented in Enclosure 3 demonstrate that Modified Alloy 718 material is comparable to Alloy X-750 material (or SB-637 Grade 688 Type 3; now referred to as UNS N07750). provides additional details of the Modified Alloy 718 material, including descriptions of the modified heat treatment process and SCC resistance. Attachment 1 of Enclosure 6 also includes an evaluation of conformance with BWRVIP-84, Revision 1 (Reference 1).

The information provided in Enclosures 3, 4, and 6 indicates that the Modified Alloy 718 material has the following attributes as compared to Alloy X-750:

" Higher resistance to SCC initiation

• Higher resistance to low temperature SCC (BWRVIP-84)

• Higher resistance to SCC crack growth (BWRVIP-138, Revision 1 (Reference 2))

• Similar strength and hardness

• Higher ductility

• Superior fatigue and spring properties

" Similar irradiation relaxation rate Based on the above comparison, the proposed change ofjet pump holddown beam material from Alloy X-750 to Modified Alloy 718 will not affect the design function of the holddown beams and will improve the beams' resistance to SCC.

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ENCLOSURE 1 EVALUATION OF THE PROPOSED CHANGE Inspection intervals for the Modified Alloy 718 holddown beam are not currently addressed in BWRVIP-138. NMPNS will be performing evaluations to establish inspection intervals for the Modified Alloy 718 holddown beam and expects that inspection intervals similar to those for Group 3 beams in BWRVIP-1 38 can be demonstrated. In accordance with BWRVIP guidelines, NMPNS will submit to the NRC an evaluation to support establishment of inspection intervals for the new holddown beams in accordance with criteria contained in the latest revision of BWRVIP-41, "BWR Vessel and Internals Project, BWR Jet Pump Assembly Inspection and Flaw Evaluation Guidelines." Basing the inspection intervals on the latest BWRVIP-41 criteria is consistent with USAR Section 3.9B.5.1.2 and USAR Appendix C, Section C.1.12. This NMPNS evaluation will be submitted approximately one year prior to the next scheduled NMP2 refueling outage following installation of the Modified Alloy 718 jet pump holddown beams.

4.0 REGULATORY EVALUATION

4.1 Applicable Regulatory Requirements/Criteria General Design Criterion (GDC) 1, "Quality standards and records," requires that structures, systems and components (SSC) important to safety be designed, fabricated, and tested to quality standards commensurate with the importance of the safety functions to be performed, and that, where generally recognized codes and standards are used, they be identified and evaluated to determine their applicability, adequacy, and sufficiency, and are supplemented or modified as necessary to assure a quality product in keeping with the required safety function.

10 CFR 50.55a, "Codes and standards," requires that SSCs be designed, fabricated, erected, constructed, tested, and inspected to quality standards commensurate with the importance of the safety function to be performed. This regulation identifies editions and addenda of the ASME Boiler and Pressure Vessel Code that have been approved for incorporation by reference, and also identifies regulatory guides that identify ASME Code Cases approved for use by the NRC.

The jet pump assemblies, including the holddown beams, are reactor vessel internals, but are not core support structures. They are not ASME code components, but are fabricated from ASTM or ASME specification materials. This is consistent with the acceptance criteria in SRP Section 4.5.2, which states that for core support structures and reactor internals, the permitted material specifications are those given in the ASME Code Section III, Division 1, with properties of these materials specified in the ASME Code Section II. In addition, the SRP states that additional permitted materials are identified in ASME Code Cases approved for use by an NRC regulatory guide. The Modified Alloy 718 material has been included in ASME Code Case N-60-6, "Material for Core Support Structures,Section III, Division 1." This Code Case revision was approved by ASME on December 6, 2011; however, it has not yet been approved for use by the NRC in a regulatory guide (i.e., Regulatory Guide 1.84). The evaluations provided in Section 3.0 above demonstrate that the Modified Alloy 718 material has similar or improved properties as compared to the existing Alloy X-750 material, thereby assuring a quality component in keeping with the required function of the jet pump assemblies.

4.2 Significant Hazards Consideration Nine Mile Point Nuclear Station LLC (NMPNS) is requesting an amendment to Renewed Facility Operating License NPF-69 for Nine Mile Point Unit 2 (NMP2). The proposed amendment would revise the NMP2 licensing basis to allow for the use of a new material, Modified Alloy 718, for the reactor recirculation system jet pump holddown beam that is not currently described in the NMP2 Updated Safety Analysis Report (USAR).

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ENCLOSURE 1 EVALUATION OF THE PROPOSED CHANGE NMPNS has evaluated whether or not a significant hazards consideration is involved with the proposed amendment by focusing on the three standards set forth in 10 CFR 50.92, "Issuance of Amendment," as discussed below:

1. Does the proposed amendment involve a significant increase in the probability or consequences of an accident previously evaluated?

Response: No.

The proposed change is limited to replacement of the existing jet pump holddown beam material with Modified Alloy 718 material. The jet pump assemblies are not considered an initiator of any previously evaluated accident. The jet pumps are passive devices that direct reactor coolant flow to the core during normal plant operation and function to maintain the ability to reflood the reactor to two-thirds core height following a loss of coolant accident (LOCA). The Modified Alloy 718 material has similar or improved material properties compared to the existing jet pump beam material (Alloy X-750). Thus, the jet pump holddown beams fabricated from the Modified Alloy 718 material are no more likely to fail than the existing jet pump beams, thereby assuring that the jet pump assemblies will continue to function to maintain the ability to reflood the reactor to two-thirds core height following a LOCA. In addition, the material change does not affect the design or operation of any accident mitigation system. Therefore, neither the types or amounts of radiation released nor the predicted radiological consequences of previously evaluated accidents will be affected.

Based on the above discussion, it is concluded that the proposed amendment does not involve a significant increase in the probability or consequences of an accident previously evaluated.

2. Does the proposed amendment create the possibility of a new or different kind of accident from any accident previously evaluated?

Response: No.

The proposed change is limited to the replacement of the existing jet pump holddown beam material with Modified Alloy 718 material. The proposed change does not affect any material-related failure mechanisms or malfunctions that could be associated with the jet pump holddown beam and does not affect the design function of the beam to apply a downward clamping force on each inlet subassembly to resist the elbow and nozzle hydraulic reaction forces during normal operation.

The material change does not affect the ability of the jet pump assemblies to function to maintain the ability to reflood the reactor to two-thirds core height following a LOCA, and does not affect the design function or operation of any plant system or component. The proposed material change also does not introduce any new or different plant operating modes, and does not change any setpoints that would alter the dynamic response of plant equipment. Therefore, the jet pump holddown beam material change does not introduce any new or different accident initiation mechanisms.

Based on the above discussion, it is concluded that the proposed amendment does not create the possibility of a new or different kind of accident from any accident previously evaluated.

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ENCLOSURE 1 EVALUATION OF THE PROPOSED CHANGE

3. Does the proposed amendment involve a significant reduction in a margin of safety?

Response: No.

The proposed change is limited to replacement of the existing jet pump holddown beam material with Modified Alloy 718 material. The Modified Alloy 718 material has similar or improved material properties compared to the existing material such that the jet pump assembly design functions are not adversely affected. The proposed change does not alter any setpoints at which protective actions are initiated, and there are no changes to the design or operational requirements for systems or equipment assumed to operate for accident mitigation.

Based on the above discussion, it is concluded that the proposed amendment does not involve a significant reduction in a margin of safety.

Based on the above, NMPNS concludes that the proposed amendment does not involve a significant hazards consideration under the standards set forth in 10 CFR 50.92(c), and, accordingly, a finding of "no significant hazards consideration" is justified.

4.3 Conclusions In conclusion, based on the considerations discussed above, (1) there is reasonable assurance that the health and safety of the public will not be endangered by operation in the proposed manner, (2) such activities will be conducted in compliance with the Commission's regulations, and (3) the issuance of the amendment will not be inimical to the common defense and security or to the health and safety of the public.

5.0 ENVIRONMENTAL CONSIDERATION

A review has determined that the proposed amendment would change a requirement with respect to installation or use of a facility component located within the restricted area, as defined in 10 CFR 20.

However, the proposed amendment does not involve: (i) a significant hazards consideration, (ii) a significant change in the types or significant increase in the amounts of any effluent that may be released offsite, or (iii) a significant increase in individual or cumulative occupational radiation exposure.

Accordingly, the proposed amendment meets the eligibility criterion for categorical exclusion set forth in 10 CFR 51.22(c)(9). Therefore, pursuant to 10 CFR 51.22(b), no environmental impact statement or environmental assessment need be prepared in connection with the proposed amendment.

6.0 REFERENCES

1. BWRVIP-84, Revision 1, "BWR Vessel and Internals Project, Guidelines for Selection and Use of Materials for Repairs to BWR Internal Components," August 2011

2. BWRVIP-138, Revision 1, "BWR Vessel and Internals Project, Updated Jet Pump Beam Inspection and Flaw Evaluation Guidelines," December 2008 5 of 5

ATTACHMENT 1 PROPOSED CHANGES TO THE NINE MILE POINT UNIT 2 UPDATED SAFETY ANALYSIS REPORT (USAR)

(MARK-UP)

The current versions of Nine Mile Point Unit 2 USAR pages 4.5-6, 4.5-8, and 4.5-9 have been marked-up by hand to reflect the proposed changes. Page 4.5-5 is provided for information only and does not include a markup. Following NRC approval of the license amendment request, the USAR will be updated to incorporate these proposed changes in accordance with 10 CFR 50.71(e).

Nine Mile Point Nuclear Station, LLC December 30, 2011

Nine Mile Point Unit 2 USAR * , j-1 \

Control rod drive ASME SA-312, Type 304 and housing ASME SA-182, Type 304 Control rod guide tube ASTM A351 or ASME SA-351, Type CF8, ASME SA-358, SA-312, SA-249, and ASTM A312, A240, A276, A269, A358 (Type 304)

Orificed fuel support ASME SA-351, Type CF8 Materials employed in other reactor internal structures include:

1. Stpm Rpparatnr and Stpam Dryer All materials are 300 series stainless steel:

Plate, sheet, and ASTM A240, Type 304 or 316L strip Forgings ASTM A182, Grade F304 Bars ASTM A276, Type 304 or 316L Pipe ASTM A312, Grade TP 304 Tube ASTM A269, Grade TP 304 Bolting material ASTM A193, Grade B8 Nuts ASTM A194, Grade 8 Castings ASTM A351, Grade CF8 (Type 304)

2. .Tat Plump Annpmhi as The components in the jet pump assemblies are a riser, inlet mixer, diffuser, and riser brace. Materials used for these components are to the following specifications:

Castings ASTM A351, Grade CF8 and ASME SA-351, Grade CF3 ASTM A194, Grade 8 or 8M Bars ASTM A276, Type 304 ASME SA-479, 316L ASTM A479, 304L Bolts ASTM A193, Grade B8 or B8M Sheet and plate ASTM A240, Type 304, and ASTM A240, Type 304L Tubing ASTM A269, Grade TP 304 USAR Revision 10 4.5-5 November 1998

Nine Mile Point Unit 2 USAR Pipe ASTM A358, Type 304, ASTM A312, Type 304, and ASME SA312, Grade TP 304 welded fittings ASTM A403, Grade WP304 Forging ASME SA-182, Grade F304, ASTM B166, and ASTM A637, Grade 688 Materials in the jet pump assemblies that are not Type 304 stainless steel are listed below:

a. The inlet mixer adaptor casting, wedge casting, bracket casting, adjusting screw casting, and diffuser collar casting are Type 304 hard surfaced with Stellite 6 for slip fit joints.

b. The diffuser is a bimetallic component made by welding a Type 304 forged ring to a forged Inconel 600 ring, made to Specification ASTM B166.

c. The inlet-mixer contains a pint insertC3iý made of Inconel X-750 to Specification ASTM A637, Grade 688, or ASTM B637, Grade UNS N07750, Type 3.

3. Core Spray Spargers and Core Spray Lines Materials used for these components are:

ASME SA-312 Type 304L for core spray spargers.

ASME SA-376 Type 316L for core spray lines.

All core support structures are fabricated from ASME- and ASTM-specified materials and designed using ASME Section III as a guide. The other reactor internals are noncoded and are fabricated from ASTM or ASME specification materials. Material requirements in the ASTM specifications are identical to requirements in corresponding ASME material specifications.

4.5.2.2 Controls on Welding Requirements of ASME Boiler and Pressure Vessel Code,Section IX, are followed in fabrication of core support structures and other internals.

4.5.2.3 Nondestructive Examination of Wrought Seamless Tubular Products Wrought seamless tubular products for CRD guide tubes, CRD housings, and peripheral fuel supports were supplied in USAR Revision 18 4.5-6 October 2008

Nine Mile Point Unit 2 USAR The degree of cleanliness obtained by these procedures is assessed to meet the requirements of RG 1.37.

Regulatory Guide 1.44 All wrought austenitic stainless steel was purchased in the solution heat-treated condition. Heating above 800OF was prohibited (except for welding) unless the stainless steel was subsequently solution annealed. For Type 304 steel with carbon content in excess of 0.035 percent carbon, purchase specifications restricted the maximum weld heat input to 110,000 joules/in, and the weld interpass temperature to 350OF maximum.

Welding was performed in accordance with Section IX of the ASME Boiler and Pressure Vessel Code. These controls were employed to avoid severe sensitization and are assessed to meet the intent of RG 1.44.

Regultory Guide 1.71 There are few restrictive welds involved in the fabrication of items described in this section. Mockup welding was performed on the welds with most difficult access.

Mockups were examined with radiography or by sectioning.

4.5.2.5 Other Materials Hardenable martensitic stainless steels and precipitation-hardening stainless steels are not used in the reactor internals.

Materials, other than Type 300 stainless steel, employed in vessel internals are:

SB-166, SB-167, and SB-168 nickel-chrome-iron (Inconel 600)

SA-637, Grade 688 (Inconel X-750). IAA -I i Inconel 600 tubing plate and sheet are used in the annealed condition. Bar may be in the annealed or cold-drawn condition.

Inconel X-750 components are fabricated in 0the annealed or equalized condition and aged 20 hr at 1,300 F. Ve4 ,

Stellite 6 hard surfacing is applied to austenitic stainless steel castings using the gas tungsten arc welding or plasma arc surfacing processes.

4.5.3 Control Rod Drive Housing Supports All CRD housing support subassemblies are fabricated of ASTM A-36 structural steel, except for the following items:

USAR Revision 18 4.S-8 October 2008

INSERT 1 (for NMP2 USAR Section 4.5.2.1; page 4.5-6)

d. The jet pump beam is fabricated from Modified Alloy 718 material, specified as Grade 718 Type 2 in ASME Code Case N-60-6. Use of this material for the jet pump beams was approved in License Amendment No. XXX (Reference 1).

INSERT 2 (for NMP2 USAR Section 4.5.2.5; page 4.5-8)

Modified Alloy 718 components are solution annealed and precipitation hardened for 6 hr at 1,300 0 F.

Nine Mile Point Unit 2 USAR Item Material Grid ASTM A-441 Disc springs Schnorr, Type BS-125-71-8 Hex bolts and nuts ASTM A-307 6 x 4 x 3/8 tubes ASTM A-500, Grade B For further CRD housing support information, refer to Section 4.6.1.2.

4All, 1 USAR Revision 18 4.S-9 October 2008

ENCLOSURE 2 LIST OF REGULATORY COMMITMENTS Nine Mile Point Nuclear Station, LLC December 30, 2011

ENCLOSURE 2 LIST OF REGULATORY COMMITMENTS The following table identifies the regulatory commitments in this document. Any other statements in, this submittal represent intended or planned actions. They are provided for information purposes and are not considered to be regulatory commitments.

REGULATORY COMMITMENT DUE DATE In accordance with BWRVIP guidelines, NMPNS will submit to the March 1, 2013 NRC an evaluation to support establishment of inspection intervals for the new holddown beams in accordance with criteria contained in the latest revision of BWRVIP-41, "BWR Vessel and Internals Project, BWR Jet Pump Assembly Inspection and Flaw Evaluation Guidelines." This NMPNS evaluation will be submitted approximately one year prior to the next scheduled NMP2 refueling outage following installation of the Modified Alloy 718 jet pump holddown beams.

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ENCLOSURE 3 TOSHIBA CORPORATION RECORD 10-1516 CODE CASE REVISION Nine Mile Point Nuclear Station, LLC December 30, 2011

Record # 10-1516 PSN-2011-0561 PM-2010-0348 Rev.2 May, 2011 (Rev. 070911)

Toshiba Corporation

Subject:

Code Case Revision Scope: Code Case N-60-5, Material for Core Support Structures,Section III, Division 1 Request: Add Modified Alloy 718 material to Code Case N-60-5, Material for Core Support Structures,Section III, Division 1. The values shown in the markups, of Tables A, B and C from the Code Case, below shall be included in Code Case N-60-5. The nomenclatures for these tables correspond to the Tables in Code Case N-60-5.

Background 1: The materials utilized for light water reactors core support structures constructed to the requirements of Subsection NG of Section III, Division 1 are those listed in Tables 2A and 2B,Section II, Part D, Subpart 1. Code Case N-60-5 lists additional materials that can be utilized for core support structures constructed to the requirements of Subsection NG of Section III, Division 1.

Currently material SB-637 modified alloy 718 is not listed in Section II, Part D, Subpart 1 or Code Case N-60-5. However, a material with similar yield and tensile strength properties, SB-637 Grade 688 (now referred to as UNS N07750) Type 3 is listed in Code Case N-60-5. Modified alloy 718 has high strength satisfied with the requirements of the strength value comparable to SB-637 Grade 688 Type 3.

The following material properties for modified alloy 718 are required for inclusion into Code Case N-60-5.

• Yield Strength values (Sy) at temperature

• Tensile Strength values (Su) at temperature

• Stress Intensity values (Sm) at temperature The first step was to calculate the Yield Strength values (Sy) and Tensile Strength values (Su) at temperature. Then the Stress Intensity values (Sm) at temperature were calculated in accordance with ASME Section II, Part D, Mandatory Appendix 2.

The calculations of material properties are documented in Attachment 1 of this request.

The results of these calculations were compared to those of the SB-637 Grade 688 Type 3 material, with similar yield and tensile strength Properties, and found to be very comparable, as shown in Figures 4, 5 and 6 in Attachment 1. In addition, three heats of tensile test data as a function of temperature were provided and analyzed with the BPV IITG Data Analysis software tool to calculate yield and tensile strength trend curves, in addition to the required Design Stress Intensity values for the Modified 718 Alloy (Pages 29 thru 35 of this document). Therefore, it is concluded that the Modified Alloy 718 material properties proposed herein are suitable for incorporation into Code Case N 5 for the construction of core support structures in accordance with Section III, Div. 1, Subsection NG, Class CS rules.

Page 1 of 3 Page 1/44

Background 2: In addition to above tensile data, the following material properties for modified alloy 718 are required in ASME Section II, Part D, Mandatory Appendix 5, Guideline on the Approval of New Materials under the ASME Boiler and Pressure Vessel Code.

• Fatigue data over the range of design temperatures

• Coefficient of thermal expansion over the range of temperatures for which the material is to be used

• Thermal conductivity and diffusivity over the range of temperatures for which the material is to be used

• Young's modulus over the range of temperatures for which the material is to be used

• Poisson's ratio over the range of temperatures for which the material is to be used

• Shear modulus over the range of temperatures for which the material is to be used Fatigue data are document in Attachment 2 of this request. Fatigue data were compared to existed design fatigue curves for austenitic steels, nickel-chromium-iron alloy, nickel-iron-chromium alloy, and nickel-copper alloy in ASME Sec. III, Division 1, Mandatory Appendix I. Fatigue data of modified alloy 718 located above the ASME design fatigue curves, which were conservative for modified alloy 718, as shown in Figure A2-1 in Attachment 2. Therefore, it is concluded that modified alloy 718 can be applied the existed ASME design fatigue curves and is suitable for use in construction of core support structures.

Other properties of coefficient of thermal expansion, thermal conductivity and diffusivity, Young's modulus, Poisson's ratio, shear modulus and density are document in of this request. The data of modified alloy 718 were compared to those of the conventional material SB-637 Grade 718 (now referred to as UNS N07718) and the equivalent material SB-637 Grade 688 (now referred to as UNS N07750) in ASME Sec. II, Part D, and found to be very comparable, as shown in Figures A3-1, A3-2, A3-3, A3-4 and Table A3-2 in Attachment 3. Therefore, it is concluded that the other properties proposed herein are suitable for use with modified alloy 718 used in construction of core support structures.

Page 2 of 3 Page 2/44

Table A Stress Intensity, Kips/sq in. (MPa) for Metal Temperature,

° F (°C), Not to Exceed Nominal P No Prod. Spec. Type or Notes i Min. Unit. 100 200 300 400 500 600 650 700 750 800 Composition Form No. Grade tYield Tens. Str. (38) (93) (149) (204) (260) (316) (343) (371) (399) (427) 718 100 160 53.3 53.3 53.3 53.3 52.3 51.2 50.7 50.1 49.5 48.8 Type 2 (689) (1103) (368) (368) (368) (368) (361) (353) (349) (345) (341) (336)

NOTES:(16) Chemical composition of Grade 718 Type 2 is same as that of conventional Grade 718 (Type 1). Heat treatment condition of Type 2 is modified for that of Type 1.

Table B Yield Strength Values Sy Yield Strength, Kips/sq in. (MPa) for Metal Temperature,

° F (°C), Not to Exceed Nominal Prod. Type Spec. 100 200 300 400 500 600 650 700 750 800 Composition Form Spec. No. or Notes Min. (38) (93) (149) (204)(260) (316) (343)(371) (399) (427)

Grade Yield Ni-Cr-Fe 718 2 100.0 93.3 (633) 95.4 (643) 98.6 (658) 90.1 (618) 90.9 (621) 91.9 (627) 88.4 87.5 89.1 (609) 89.6 (614)

Cb - Type (689) (680) (603) 0,,

NOTES:(10) Chemical composition of Grade 718 Type 2 is same as that of conventional Grade 718 (Type 1). Heat treatment condition of Type 2 is modified for that of Type 1.

Table C MATERIALS PROPERTIES, SUBSECTION NG TENSILE STRENGTHS, Su Tensile Strength Values, Su, Kips/sq in. (MPa) for Austenitic Steel and High Nickel Alloys for Class 1 Components Thmnerature ~ (O(~

Nominal Prod. Spec. Type or Spec. 100 200 300 400 500 600 650 700 750 800 Composition Form No. Grade T.S. (38) (93) (149) (204) (260) (316) (343) (371) (399) (427) 718 160.0 160.0 160.0 160.0 160.0 157.0 153.7 152.0 150.2 148.4 146.4 N Type2 (1103) (1103) (1103) (1103) (1103) (1082) (1060) (1048) (1036) (1023) (1009)

NOTE: Chemical composition of Grade 718 Type 2 is same as that of conventional Grade 718 (Type 1). Heat treatment condition of Type 2 is modified for that of Type 1.

FFBS-Fittings, Forgings, Bars, Shapes

ATTACHMENT- 1 Page AM-i of Al-11 Page 4/44

Calculations of Sy, Su, Sm values: The first step was to calculate the Yield Strength values (Sy) and Tensile Strength values (Su) at temperature based on the tensile test data provided from three heats of material. Chemical compositions of three heats of material (Heat ID A, B and C ) used in tensile tests are shown in Table Al-1. The tensile test method employed was JIS (Japanese Industrial Standards) test method. Test temperatures were room temperature (20 0C), 75°C, 100°C, 150°C, 200°C, 250°C, 275°C, 300°C, 325-C, 3500 C, 400 0C and 425 0C, and converted to Fahrenheit temperatures. Tensile tests were conducted three times for each heat and temperature. Tensile data of modified alloy 718 are listed in Table A1-2. Tensile test data of yield strength ( a y) and tensile strength ( a u) at temperature are shown in Figure Al-1. Average temperature dependent trend curves of yield strength ( a y) and tensile strength ( a u) were obtained based on the average value for three heats of material in each temperature as shown in Figure A1-2. They were normalized by the yield strength ( a y) and tensile strength ( a u) in room temperature (20 0C) respectively, and Ry, RT values at temperature were obtained as shown in Figure A1-3.

where Ry =ratio of the average temperature dependent trend curve value of yield strength to the room temperature yield strength RT =ratio of the average temperature dependent trend curve value of tensile strength to the room temperature tensile strength Yield Strength values (Sy) shown at temperature in Table B are the least of the following:

(1) Sy: Minimum yield strength at room temperature specified in ASME/ASTM SB-637/B637 for equivalent material Grade 688 Type 3 (100ksi)

(2) RyX Sy Tensile Strength values (Su) shown at temperature in Table C are the least of the following:

(1) ST: Minimum tensile strength at room temperature specified in ASME/ASTM SB-637/B637 for equivalent material Grade 688 Type 3 (160ksi)

(2) RTXSTX 1.1 Then the Stress Intensity values (Sm) shown at temperature in Table A were calculated in accordance with ASME Section II, Part D, Mandatory Appendix 2.

The results of these calculations were compared to those of the equivalent material SB-637 Grade 688 Type 3 as shown in Figures A1-4, A1-5 and A1-6. Yield strength ( a y, Sy) and tensile strength (a u, Su) at temperature were summarized in Figure A1-7.

Page A1-2 ofAl-I 1 Page 5/44

Table Al-I Chemical compositions of three heats of material p ofnain Chemical Composition (W)

C Si Mn P S Ni Cr Co Mo Nb+Ta CU AI T, B Fe max max max max max 50.0 17.0 max 2.80 4.75 max 0.20 0.65 max I I l l IBal Heat ID 0.08 0.35 0.35 0.015 0.015 -55.0 -21.0 1.0 -3.30 -5.50 0.30 -0.80 -1.15 0.006 A 0.03 0.10 0 .04 0004 0.0003 52.41 18.59 0.03 3.07 5.12 0.01 0.52 0.95 0.0048 Bal B 0.03 0.08 0.04 0.004 0.0002 52.49 18.65 0.02 3.08 5.07 0.01 0.55 0.94 0.0038 Bal C 0.03 0.06 004 0003 0.0001 52.34 18.69 0.03 309 5.11 0.02 0.54 0.96 0.0042 Bal ASME/ASTM SB-637/8637 alloy UNS N07718 (Grade 718)

• Solution Heat Treatment: 1030'C X 1 h O.C

• Precipitation Hardening Heat Treatment: 704°C X 6h A.C Page A1-3 of Al-l1 Page 6/44

Table A1-2 Tensile data of modified alloy 718 1-I Heat ID Test Temperature Test A C (OFt Io*

167 1143 167 1145 212 1142 52.A 212 1126 212 1126 2 5M.

302 1116 55E 302 1116 15. 1 53.E 31.8 535 183 61.0 7746V8 1250.0 1 302 331 47108.4 53 9, 33.9 55.11 108.71 749.51 148.71 1 52.,

392 52.1 392 200 1 47.4

> 482 250 1 53.E 482 250 1 52.,

57.Z 0

527 55.f

> 527 52.4 527 54.7 572 52.2 572 52.2 572 52.4 617 56.C 617 149.81 1033 744.3 141.8 56.C

-33.41 54.8 55.3 103.91 1016.,0 731.1 140.5 617 148.31 1022 329 662 146.3 I 1009 32.91 55.31 103.91 716.3 137.7 9973 7.Q. 53.6 662 148.71 1025] 32.1 56.21 141.3 97. 681 54.(

662 148.81 1026 35.31 54.71 104.8F 722.7 139.01 958.1 1 36.31 56.7 752 145.31 1002] 33.71 55.11 4 136.2 939.21 38.8 531 752 400 2 109.2 752.61 139.01 958.2 33.91 54.9 116.71 804.31 143.71 990.7 1 34.31 55.51 103.81 715.5 135.8 936.5 I 35.01 53."

752 110.1 138.7 30 1 .91 806.2 143.81 32.81 55.5 104.31 719.41 136.9] 944.1 [ 32.7 53.1 797 425 11 109.2 753.11 138.71 956.0T 32.11 53.3 117.41 809.21 143.51 989.61 33.4 55.61 101.71 701.5 134.0 923.8 1 37.01 53.E 797 429- 2 105.0 72391 134.8 38.5 .01 820.81 1448 30.51 54.71 102.1 703.7 [ 133.7] 921.6 [ 36.6 52.1 797 425 3 112.2 773.4 141.4 975.01 35.61 52.61 116.61 804.1 1 143.1 1 986.3 1 34.6 56.01 109.01 751.3 1 137.7 1 949.6 1 33.71 54.4

1400 OA

-; 1200 AB-c 1000 b 800 AA A A 600

• ~400

.* 200 0

0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature(* F) 1400 o~1200 1000 b

..:- 800 c0 600 D c II 400 200 0

0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature( 0 F)

Fiaure Al-I Tensile test data of vield strenath and tensile strength at temperature Page AI-5 of Al-Il Page 8/44

1400 c 1200 1000 b 800 Q 600 I Average

.+jn 400

• 200 0

0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature( 0 F) 1400 n 1200 [ *Average

. 1000 b

_ 800 a 600 4 -J m 400 co, c 200 0

0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature(' F)

Figure A1-2 Average temperature dependent trend curves of yield strength and tensile strength Page AI-6 ofAl-11 Page 9/44

1.2

• Average]

1.0 0.8 n-0.6 0.4 0.2 0.0 0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature(* F) 1.2 1.0 ---[ý*oýAveragýe 0.8 0.4 0.2 0.0 0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature ( 0 F)

Figure A1-3 Ry, RT values at temperature Page AI-7 of Al-il Page 10/44

200 180 160 140 120

>100 -*-

c,80 60 Alloy 718 40 *Modified 20 X ASME Code CASE N-60-5 SB637 Grade 688 Type 3(Alloy X-750) 0 ' 1 . I I 0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature( 0 F)

Fiaure AI-4 Yield Strenath values at temDerature Page A1-8 ofAl-1I1 Page 11/44

200 180 160 140 120

-U 100 C,, 80

1. SModified 60 Alloy 718 S 40 20 XASME Code CASE N-60-5 SB637 Grade 688 Type 3(AIloy X-750) K n I I I I I III 0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature(' F)

Figure AI-5 Tensile Strength values at temperature Page AI-9 ofAl-1I1 Page 12/44

100 90 *Modified Alloy 718 80 XASME Code CASE N-60-5 SB637 Grade 688 Type 3(Alloy X-750) 70

.- I 60

~ ___

50 E

(n 40 30 20 10 0 IIII I I II 0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature( 0 F)

Figure A1-6 Stress Intensity values at temperature Page Al-1O of Al-I1 Page 13/44

200 180 160 140 A 06 P-, ý, AAWAA 120 LZI A A U) 100 b>80 60 O cry (Modified Alloy 718 (Heat A))

• cry (Modified Alloy 718 (Heat B))

40 ] o (ry(Modified Alloy 718 (Heat C))

• 0-y (Modified Alloy 718 (Average of Heats A, B, C))

• Sy (Modified Alloy 718) 20 X Sv (ASME Code CASE N-60-5 SB637 Grade 688 Tvye 3(Allov X-750))

0 L I ' I I I l 0 100 200 300 400 500 600 700 800 900 Fahrenheit temperature(0 F) 200 180 160 140 AA

- 120 co 100 S80 O UTu (Modified Alloy 718 (Heat A))

b 60 A UTu (Modified Alloy 718 (Heat B))

• UTu (Modified Alloy 718 (Heat C))

40

• 0-u (Modified Alloy 718 (Average of Heats A, B, C))

• Su (Modified Alloy 718) 20 X Su (ASME Code CASE N-60-5 SB637 Grade 688 Type 3(Alloy X-750))

I I I I I 0 II I - I 0 100 200 0300 400 500 600 700 800 900 Fahrenheit temperature( 0 F)

Fiaure AI-7 Yield strenath (a v. Sv) and tensile strenath (a u, Su) at temperature Page AI- lI of Al-Il Page 14/44

ATTACHMENT- 2 Page A2-1 of A2-5 Page 15/44

Fatigue data: Fatigue tests from three heats of modified alloy 718 were conducted in order to compare to existed design fatigue curves for austenitic steels, nickel-chromium-iron alloy, nickel-iron-chromium alloy, and nickel-copper alloy in ASME Sec.

III, Division 1, Mandatory Appendix I. Same three heats of material used in tensile tests (see Attachment 1) were used in the fatigue tests. Chemical compositions of three heats of material (Heat ID A, B and C) used in fatigue tests are shown in Table A2-1. Test temperatures were room temperature (21-26°C(70-790 F)) and BWR design temperature (3020 C(5760 F)). Load-controlled fatigue tests (stress ration: -1) were conducted in accordance with ASTM E 466 under the condition of the stress amplitude below the yield strength. Test specimens based on ASTM E 466 Fig.1 were used in load-controlled fatigue tests. Strain-controlled fatigue tests (strain ratio: -1) were conducted in accordance with ASTM E 606 under the condition of the stress amplitude beyond the yield strength. Test specimens based on ASTM E 606 Fig.1 were used in strain-controlled fatigue tests. In the strain-controlled fatigue tests, stress value ( a )

was calculated from strain value ( E ) and Young's modulus (E) based on Figure A3-3 in . (a = E E, E (RT)= 203GPa (29.4 X 106 psi), E (302°C(576°F))= 191GPa (27.7 x 106 psi))

Fatigue data of modified alloy 718 are listed in Table A2-2. In Figure A2-1, fatigue data were compared to the existed design fatigue curves for austenitic steels, nickel-chromium-iron alloy, nickel-iron-chromium alloy, and nickel-copper alloy in ASME Sec.

III, Division 1, Mandatory Appendix I. Fatigue data of modified alloy 718 located above the ASME design fatigue curves, which were conservative for modified alloy 718.

Page A2-2 of A2-5 Page 16/44

Table A2-1 Chemical compositions of three heats of material peioton* ____ Chemical Composition (5)

C Si Mn P S Ni Cr Co Mo Nb+Ta Cu AJ T1 B Fe max max max max max 50.0 17.0 max 2.80 4.75 max 0.20 0.65 max 0.35 0.015 0.015 -55.0 -21.0 1.0 -3.30 -5.50 0.30 -0.80 -1.15 0.006 HeatID 0.08 0.35 A 0.03 0.10 0.04 0.004 0.0003 52.41 18.59 0.03 3.07 5.12 0.01 0.52 0.95 0.0048 Bal 02 B 0.03 0.08 0.04 0.004 0.0002 52.49 18.65 0. 3.08 5.07 0.01 0.55 0.94 0.0038 Bal C 0.03 0.06 0.04 0.003 0.0001 52.34 18.69 0.03 3.09 5.11 0.02 0.54 0.96 010082 Bal

• ASME/ASTM SB-637/B637 alloy UNS N07718 (Grade 718)

• Solution Heat Treatment: 1030°C X 1 h O.C

• Precipitation Hardening Heat Treatment: 7049C X 6h A.C Page A2-3 of A2-5 Page 17/44

Table A2-2 Fatigue data of modified alloy 718 Test Temperature Stress Amplitude Strain Fatigue Life Heat ID Amplitude (Fracture) Remarks*

(°F) (CC) (ksi) (MPa) (%) (Number of cycles) 78 26 131 900 0.44 2.03x1O4 (1)

A RT 76 24 87 600 - 1.89x 105 (2) 77 25 73 500 6.88x105 (2) 75 24 435 3000 1.48 8.89x102 (1) 71 22 218 1500 0.74 3.29x103 (1) 74 23 131 900 0.44 1.25x 104 (1)

RT5 76 24 87 600 - 1.63x 105 (2)

B 76 25 73 500 7.21x 105 (2) 72 22 65 450 4.60x 106 (2)

BWR 576 302 131 900 0.47 1.17x1O4 (1)

Design 576 302 87 600 5,57x104 (2)

Temp. 576 302 73 500 1.98x105 (2) 70 21 131 900 0.44 1.07xi10 4 (1)

C RT 76 24 87 600 - 8.00x 104 (2) 72 22 73 500 - 3.18x105 (2)

(1) Strain-Controlled fatigue testing (Strain ration: -1)

Stress value (a) was calculated from strain value (E) and Young's modulus (E).

(c=EE, E(RT)=203 GPa(29.4x 106 psi), E(302°C(576°F))=191 GPa(27.7x 106 psi))

(2) Load-Controlled fatigue testing (Stress ration: -1 )

Page A2-4 of A2-5 Page 18/44

104 Q.

(/)

1031 E

(ID 1021 I 102 103 104 105 106 107 108 Fatigue Life Nf ( Number of cycles )

(1) Strain-controlled fatigue testing (Strain ratio: -1)

(2) Load-controlled fatigue testing (Stress ratio: -1)

IFiaure A2-1 Fatique data of modified alloy 718 Page A2-5 of A2-5 Page 19/44

ATTACHMENT- 3 Page A3-1 of A3-9 Page 20/44

Other properties: Other properties of coefficient of thermal expansion, thermal conductivity and diffusivity, Young's modulus, Poisson's ratio, shear modulus and density were obtained from three heats of modified alloy 718. Same three heats of material used in tensile tests and fatigue tests (see Attachment 1 and 2) were used in the property tests. Chemical compositions of three heats of material (Heat ID A, B and C) used in the property tests are shown in Table A3-1. The property test methods employed were JIS (Japanese Industrial Standards) test methods. Test temperatures were room temperature (20 0C), 1000 C, 200 0 C, 300'C, 400°C and 4250 C, except for the testing of thermal conductivity and diffusivity, and density. Thermal conductivity and diffusivity were obtained at room temperature (20 0C), 200 0C and 4250C. Density was obtained at room temperature (20 0C). Test temperatures were converted to Fahrenheit temperatures.

Instantaneous coefficient of thermal expansion (coefficient A), mean coefficient of thermal expansion (coefficient B) and linear thermal expansion (coefficient C) at temperature are shown in Figure A3-1. Thermal conductivity (TC) and diffusivity (TD) at temperature are shown in Figure A3-2. Young's modulus and Poisson's ratio at temperature are shown in Figure A3-3. Shear modulus (G) data at temperature are calculated from Young's modulus (E) and Poisson's ratio (y) by the equation of G=E/2(1+ v ), and shown in Figure A3-4. Density data are shown in Table A3-2. The data of modified alloy 718 were compared to those of the conventional material SB-637 Grade 718 (now referred to as UNS N07718) and the equivalent material SB-637 Grade 688 (now referred to as UNS N07750) in ASME Sec. II, Part D, and found to be very comparable.

Page A3-2 of A3-9 Page 21/44

Table A3-1 Chemical compositions of three heats of material pooZfoo~io CPChemical Composition (%)

C Si Mp P S Mi Cr Co Mo NbpTa CU Ato B Fe max max max max max 50.0 17.0 max 2.80 4.75 max 0.20 0.65 max Bal.

0.08 0.35 0.35 0.015 0.015 -55.0 -21.0 1.0 -3.30 -5.50 030 -0.80 -1.15 0.006 A 0.03 0.10 0.04 0.004 0.0003 52.41 18.59 0.03 3.07 5.12 0.01 0.52 0.95 00048 Bal B 0.03 0.08 0.04 0.004 0.0002 52.49 18.65 0.02 3.08 5.07 0+01 0.55 0.94 0.0038 Bal C 003 006 0.04 0.003 00001 5234 18.69 0.03 3.09 5.11 0.02 0.54 0.96 0.0042 Bal

• ASME/ASTM SB-637/B637 alloy UNS N07718 (Grade 718)

• Solution Heat Treatment: 1030°C X 1h O.C

• Precipitation Hardening Heat Treatment: 704°C X 6h A.C Page A3-3 of A3-9 Page 22/44

12 11 *ICoefficient A CIL 10 x 0 9

8 0

U-0 7

6 N

4J C 5 OA

~0 4 AB Modified Alloy 718 0

3 DC I 0 ASME Sec.1l, Part.D, N07718 (Alloy 718) 4J) 2 0- x ASME Sec.i, Part.D, N07750 (Alloy X-750) cc 4J, 1 0

0 100 200 300 400 500 600 700 800 900 1000 1100 1200 Fahrenheit Temperature (C F) 12 11 - Coefficient B 10 Ql) 9

0. 8 (U~ 7 0 6 CD> 5 OA 4 AB Modified Alloy 718 3

__ __ __ C J 0 2

• ASME Sec.li, Part.D, N07718 (Alloy 718)

Ca x ASME Sec.il, Part.D, N07750 (Alloy X-750) 1 0

0 100 200 300 400 500 600 700 800 900 1000 1100 1200 Fahrenheit Temperature (C F)

Figure A3-1 Thermal expansion at temperature (1/2)

Page A3-4 of A3-9 Page 23/44

12 11 10 0 9 p 0

8 S S

7 0- 6 x 5 4

E

~OA1 AB JModified

.4-3

• m 1 Alloy 718 2

eASME Sec.Il, Part.D, N07718 (Alloy 718) 0 1 Sx ASME Sec.[l, Part.D, N07750 (Alloy X-750) 0 0 100 200 300 400 500 600 700 800 900 1000 1100 1200 Fahrenheit Temperature (C F)

Filure A3-1 Thermal expansion at temperature (2/2)

Page A3-5 of A3-9 Page 24/44

16 uL TC 14 12 ---

10x- xexxx X<

"10 S8

-~6 0OA O ARB Modified Alloy 718 C) 4 0C.

CU E 0 ASME Sec.Il, Part.D, N07718 (Alloy 718) 22 x ASME Sec.I[, Part.D, N07750 (Alloy X-750) 0 0 200 400 600 800 1000 1200 1400 1600 Fahrenheit Temperature (0 F) 0.20 X .0 X0 0 x X X x 0.15

~~~xxx*.*x *-z-x x0x 0.10 OA 5 AB Modified Alloy 718 E 0.05 DOC

• ASME Sec.il, Part.D, N07718 (Alloy 718)

I- x ASME Sec.((, Part.D, N07750 (Alloy X-750) 0.00 1 1 0 200 400 600 800 1000 1200 1400 1600 Fahrenheit Temperature (0 F)

Figure A3-2 Thermal conductivity and diffusivity at temperature Page A3-6 of A3-9 Page 25/44

40 x x 0 x 30 0X x

x x Ma 0 C0 0

-0 4-n

_3 bb 0

10 oA1 AB 0 C Modified Alloy 718

• ASME Sec.II, Part.D, N07718 (Alloy 718) 0 Co x ASME Sec.II, Part.D, N07750 (Alloy X-750) 0 1

-300 -200 -100 0 100 200 300 400 500 600 700 800 900 1000 1100 1200 Fahrenheit Temperature(° F) 0.40 0.35 0

A- 0031 Co C/)

0 a BModified Alloy 718 0.25 0 oJ

- -Typical value for ASME Sec.li, Part.D, N07718 (Alloy 718) and N07750 (Alloy X-750) 0.20 0 100 200 300 400 500 600 700 800 900 1000 Fahrenheit Temperature (* F)

Figure A3-3 Young's modulus and Poisson's ratio at temperature Page A3-7 of A3-9 Page 26/44

15 x X

" x U) 10 X.

Ui oA AB Modified Alloy 718 0 5 0C I E

• ASME Sec.Il, Part.D, N07718 (Alloy 718) x ASME Sec.li, Part.D, N07750 (Alloy X-750)

C/)

• • G=E/2(I+v) 0

-300 -200 -100 0 100 200 300 400 500 600 700 800 900 1000 1100 1200 Fahrenheit Temperature(° F)

Figure A3-4 Shear modulus at temperature Page A3-8 of A3-9 Page 27/44

Table A3-2 Density Density (lb/in. 3)

Modified Alloy 718 ASME Sec. H, Part D Heat ID N07718 N07750 A B C (Alloy 718) (Alloy X-750) 0.287 0.288 0.288 0.297 0.298 Page A3-9 of A3-9 Page 28/44

C&S Item #10-1516, SC II TG Data Analysis time-independent analysis for the Modified 718 (1/7) rrI 14 ,1 I01.0 00o.a 0o.Q A RT 122.8 163.3 35.8 56.4 A RT 127.3 168.4 38.3 55.1 A 167 117.0 158.9 38.1 56.2 A 167 122.8 162.3 36.5 54.8 A 167 117.5 159.1 38.8 55.5 A 212 123.6 160.8 32.9 53.7 A 212 121.8 158.1 30.2 53.8 A 212 116.1 156.9 39.4 55.4 A 302 115.5 153.9 36.3 54.3 A 302 115.8 155.4 37.2 53.9 A 302 112.3 151.1 35.0 56.2 A 392 110.3 147.8 33.6 54.4 A 392 110.7 150.8 37.8 54.2 A 392 115.0 151.4 32.8 54.4 A 482 113.6 148.6 37.5 54.9 A 482 111.2 145.5 32.5 54.5 A 482 114.9 149.5 35.0 51.7 A 527 118.7 150.8 30.7 53.5 A 527 112.9 147.1 34.0 53.7 A 527 110.6 146.1 32.7 48.4 A 572 110.0 143.5 33.7 55.5 A 572 113.3 144.6 29.6 53.7 A 572 118.3 148.8 33.5 54.5 A 617 113.3 144.8 35.0 55.1 A 617 111.2 142.9 32.0 52.8 A 617 117.0 148.7 34.4 53.5 A 662 108.9 141.2 36.6 50.3 A 662 107.7 139.6 35.0 53.4 A 662 113.8 144.1 33.0 53.5 A 752 111.1 141.6 34.1 52.4 A 752 109.2 139.0 33.9 54.9 A 752 110.1 138.7 30.0 54.7 A 797 109.2 138.7 32.1 53.3 A 797 105.0 134.8 35.1 53.4 A 797 112.2 141.4 35.6 52.6 Page 1 of 3 Page 29/44

C&S Item #10-1516, SC II TG Data Analysis time-independent analysis for the Modified 718 (2/7)

B RT 132.3 170.1 33.7 54.9 B RT 134.1 171.2 32.2 55.5 B RT 135.3 172.8 35.5 56.0 B 167 130.4 166.2 32.6 55.9 B 167 129.0 165.8 35.1 55.0 B 167 129.7 166.0 32.6 53.1 B 212 129.7 165.7 33.2 56.4 B 212 125.4 163.4 37.1 55.3 B 212 126.0 163.3 37.8 55.7 B 302 126.7 161.8 34.2 55.8 B 302 127.4 161.8 31.7 55.7 B 302 123.2 158.9 31.8 53.5 B 392 124.2 158.8 33.9 55.1 B 392 124.4 157.7 34.9 55.5 B 392 120.7 155.9 33.7 55.5 B 482 125.3 156.1 31.7 53.5 B 482 123.1 155.1 32.6 53.8 B 482 119.5 153.0 35.2 55.1 B 527 120.7 152.6 33.3 56.0 B 527 121.4 152.6 33.5 56.4 B 527 119.4 151.3 34.7 56.0 B 572 118.5 150.3 37.4 56.4 B 572 124.0 152.9 32.5 56.2 B 572 123.5 153.3 33.0 56.4 B 617 120.6 150.3 32.2 55.2 B 617 120.8 149.8 32.9 55.3 B 617 118.9 148.3 33.3 54.8 B 662 118.1 146.3 32.9 55.3 B 662 121.2 148.7 32.1 56.2 B 662 119.7 148.8 35.3 54.7 B 752 119.6 145.3 33.7 55.1 B 752 116.7 143.7 34.3 55.5 B 752 116.9 143.8 32.8 55.5 B 797 117.4 143.5 33.4 55.6 B 797 119.0 144.8 30.5 54.7 B 797 116.6 143.1 34.9 56.0 Page 2 of 3 Page 30/44

C&S Item #10-1516, SC II TG Data Analysis time-independent analysis for the Modified 718 (3/7)

, rIM 110.0 100.0 1+ I.Z Z0.U C RT 115.8 160.8 40.0 54.4 C RT 116.6 162.1 39.8 50.4 C 167 113.8 156.7 35.0 53.5 C 167 112.9 156.8 40.7 55.3 C 167 111.6 155.8 41.0 51.6 C 212 114.3 155.4 35.5 52.6 C 212 112.1 154.6 42.7 56.4 C 212 114.3. 156.2 40.7 53.5 C 302 111.6 151.4 36.3 55.8 C 302 110.4 150.9 36.1 53.8 C 302 108.3 150.0 37.2 53.8 C 392 108.7 148.7 35.4 52.2 C 392 109.0 148.7 37.1 52.6 C 392 111.9 150.0 35.8 47.4 C 482 108.9 145.7 32.8 53.6 C 482 106.9 145.4 39.7 52.2 C 482 105.4 144.8 39.1 57.3 C 527 102.2 140.4 40.2 55.8 C 527 105.7 142.1 33.6 52.4 C 527 110.2 144.7 34.0 54.7 C 572 106.0 143.2 39.0 52.2 C 572 106.4 142.8 38.0 52.2 C 572 109.6 142.4 34.1 52.4 C 617 104.3 140.6 39.6 56.0 C 617 108.0 141.8 34.2 56.0 C 617 106.0 140.5 36.0 56.0 C 662 103.9 137.7 37.6 53.9 C 662 108.9 141.3 36.8 54.0 C 662 104.8 139.0 36.3 56.7 C 752 102.7 136.2 38.8 53.8 C 752 103.8 135.8 35.0 53.3 C 752 104.3 136.9 32.7 53.1 C 797 101.7 134.0 37.0 53.8 C 797 102.1 133.7 36.6 52.8 C 797 109.0 137.7 33.7 54.4 Page 3 of 3 Page 31/44

Normalized Input Data Curve Fit Coefficients Contribution Heat Temp YS UTS EL RA J YS UTS _Order YS UTS Term YS _ UTS Y A 167 0.932 0.955 1.017 1.017 0.96 0.967 2 0.594 0.941 A 167 0.978 0.975 0.974 0.974 0.966 0.967 3 0.636 0.947 0___

1 1_______

-3.1889177312E-04 4A59774454E-04 1____

-0.15275 1__

-0.165723 I Cn)

A 167 0.936 0.956 1.036 1.036 0.966 0.967 4 0.636 0.947 2 -7.532763625-E07 -5.9511561236E-N -017283 -0.013654 B 167 0.973861 0.96985 0.964497 0.964497 0.966143 0.967278 5 0.636 0.947 3 5.5225715615E-OO 1.9810050690E-09 0.60694 0.217717 C,,

B 167 0.963405 0.967516 1.038462 1.038462 0.966143 0.967278 _E-12 4_41 51_ - 10 I -0.219198 i B 167 0.966633 0.968663 0.964497 0.964497 0.966143 0.9672785 3276602294E-15 2.S1466577E-15 1 434 006456 3 C 167 0.972096 0.96629 0.862777 0.862m77 0.966143 0.967278 Data Analysis @ Temp 5001VALUES o0.907600 0 35971 C 167 0.964408 0.96690611.003287 1.003287 0.966143 0.967278 1_1_1_

C 167 0.953303 0.96074 1.010682 1.010682 0.966143 0.967278 Theal. strength Ratio Yield Strength Ratio A 212 0.966 0.966 0.878 0.878 0.952 0.954 P Show Table 1 0.948 06500 0)

A 212 0.971 0.950 0.806 0.806 10.952 0.954 0 ý A 212 0.925 0.943 1.052 1.052 0.952 0.954 hwTbe2.94 0 h .2- 06300 60 212 0.969 0.967 0.982 0.982 0.952 0.954 W ShowTable 3 o.944 0L B 212 0.937 0.954 1.096 1.098 0.952 9 S T o.94W 0.900° B 212 0.941 0.953 1.118 1.118 0.9,52 0.94PSo2blN .4 i

°98 50 C 212 0.976367 0.958273 0.875103 0.875100 0.951665 0.953741 P Show Table 5 '99 w0.9360070 ,50 0, C 212 0.957574 0.95334 1.0525a8 1.052568 0.951665 0.953741.~ 0.938 oso C 212 0.957574 0.93207 1.003287 1.003287 0.951665 0.953741 0.936 0,5700_____

A 302 0.920319 0.924695 0.966861 0.968661 0.930017 0.930878 24 2 3 4 5 A 302 0.922709 0.933707 0.992883 0.992883 0.930017 0.930878 Polynomial Order Polyomial Order A 302 0.894821 0.907871 0.934184 0.934164 0.930017 0.930878- CD.

B 302 0.94 0.944 1.012 1.012 0.930 0.931 B 302 0.951 B 0.944 020.2 0.938 0.938 0.930 0.9311. 1.2 B 32 0.920 097 0.941 0.941 0.930 0.931 CD)

C 302 0.953 934 0.895 0.89 0.930 0.931 1 Y C302 0.943 0.931 0.890 0.890 0.930 0.931 1.0- -

C 302 0.925 0.925 0.917 0.917 0.930 0.931 I & .YSr CD A 392 0.879 0.88 0.897 0.897 0.918 0.913 -0 A 3902 0862 0.90 1.009 1.009 0.918 0.913 0.8-------- CD A 392 0.916 0.910 0.875 0.875 0.918 0.913 B 392 0.92755 0.926668 1.002959 1.002959 0.918256 0.9126110 B392 0.929051 0.920249 1.032544 1.032544 0.918256 0.912611 a)

B 392 0.901419 0.909745 0.997041 0.O997041 0.918256 0.912611I -

C 392 0.928531 0.916956 0.872636 0.872636 0.918256 0.912611 1 7 CD)

C 392 0.931093 0.916956 0.914544 0.914544, 0.918256 0.912611 Z 0.4 - -- -____ ____ _____

C 392 0.955866 0,924974 0.662498 0.8624981 0.918256 0.912611 A 482 0M95 0.89-3 1.001 1.001 0.912 0.896 . 0.2 - - --- ____ _

A 482 0.886 0.874 0.867 0.867 0.912 0.896 A 462 0.916 0.898 0.934 0.934 0.912 0.896 B 462 0.936 0.911 0.938 0.938 0.912 0.896 0.0 B 482 0.919 0.905 0.964 0.964 0.912 0.896 0 100 200 300 400 500 600 700 800 900 CD B 482 0.892 0.893 1.L41 1.041 0.912 0.896 Temperature (F)

C 482 0.930,239 0.898458 0.808546 0.808546 0.912104 0.89623 C 482 0.913155 0.896608 0.978636 0.978836, 0.912104 0.89623 _ _________

CD C 462 0.900342 10.892909 0.963845 0.963846 0.912104 0.89623 -11 A 527 0.945617 0.906069 0.819395 0.819395 0.909232 0.66783 _______________ __________________ CD A1 527 0.899602 0.883637, 0.907473 0.907473 0.909232 0.88783 ________1_______ __________________

A 527 0.881275 0.877829 0.872776 0.82776 0.909232 0.66783 __ ___ ______ ________ CL B 527 0.901419 0.890488 0.965207 0.985207 0.909232 0.66783 ____

a 527 0.906647 0.890488 0.991124 0.9911124 0.909232 0.66783 ___ -4 B 527 0.89171 0.882902 1.0262 126627 0.909232 0.66783 a)k C 527 0.873 0.866 0.991 0.991 099 .888 ___

CO C 527 0.90 0.7 .88 0828 90.909 0.888 _ __ __ _____________

C 527 0.941 0.892 0.838 0.636 0.909 0.86 _____

A 572 0.876 0.882 0.899 0.899 0.906 0.879 ___ ___ ___ ___ ___ ___ ____ ___ ___________ ____

-4

-0 CD

A 572 0.903 0.869 0.790 0.790 0.906 0.879 A 572 0.943 0.894 0.894 0.894 0.906 0.879 B 572 0.884989 0.877067 1.106509 1.106509 0.905603 0.878951 B 572 0.926064 0.892239 0.961538 0.961538 0.905603 0.878951 B 572 0.92233 0.894573 0.976331 0.976331 0.905603 0.878951 C 572 0.905467 0.883042 0.96138 0.96138 0.905603 0.878951 C 572 0.908884 0.880576 0.93673 0.93673 0.905603 0.878951 90 C 572 0.936219 0.878109 0.840592 0.840592 0.905603, 0.878951 A 617 0.903 0.870 0.934 0.934 0.901 0.870 cii A 617 0.886 0.859 0.854 0.854 0.901 0.870 A 617 0.932 0.893 0.918 0.918 0.901 0.870 B 617 0.901 0.877 0.953 0.953 0.901 0.870 CD)

B 617 0.902 0.874 0.973 0.973 0.901 0.870 B 617 0.888 0.865 0.985 0.985 0.901 0.870 C 617 0.890945 0.867009 0.976171 0.976171 0.900827 0.86953 C-)

C 617 10.922551 0.874409 0.843057, 0.843057, 0.900827 0.86953 C 617 0.905467 0.866393 0.887428 0.87428 0.900827 0.86953 Cn A 662 0.867729 0.848388 0.976868 0,976868 0.894883 0.859728 A 662 0.858167 0.838774 0.934164 0,9341(4084830892 AA 62 090776.85820.808.088736.87830.572 _______0.865812_______________0.880783____________________________

B 662 10.882001 0.853725 0.973373 0.973373 0.894883 10.859728 B

C 662 0.888 51 49704 0,949704 0.894883 0.859728 44379 1,044379 0.894883 0.859728 3.927 0.927 0.895 10,860 I

__ I__ __ __ _____ I _____ ___ I ___ __ 0)

C 662 0.930 0.871 0907 0.907 0.895 0.860 I I F F + I -i F 0.895 0.885 0.870 0.877 (

).89320, cn

).871541 0.87304

).877271 7 34

).88667, CD

).890941 797 0.870 A 0.833 0.857 1 0.857 0.834 A 797 0.837 0.810 0.937 0.937 0.878 0.834 CL A 797 0.894 0.850 0.950 0.950 0.878 0.834 CD B

B 797 797 0.877 0.889 0.837 0.845 0.988 0.988 0.902 1 0.902 0.878 0.878 0.834 0.834 i i -a CD B 797 0.871 0.835 1.033 1.033 0.878 0.834 1 1 1 C

C C [

797 797 797 0.868736 0.82631 0.912079 0.912079 10.87779910.834145j 0.8721531 0.82446 10.902219 10.9022191 0.87T799 10.834145 1 10.931093 0.849126 10.83073110.830731 0.877799 10.834145]1 1 1 _ Ii ___

CD, ci) 0 CL CD CL

-4

-4

A B C D E F G H I IJ K L I M N 0 P 0Q I R T Section lID Table 2A,2B US Customary Units Coefficients 2 Term YS C-)

0 1 3

4 Specifications (Enter size range hersXEnter size range hereXEnter size range herm) 1 -3.18891776259989E-04 C, 5 Type/Grade 2 .7.53276387504441E07 6 Min TS in B6 (ksi) 160 (If SI spec use hard coversions for columns D and E) 3 5.52257173325188E-09 CD 7 Min YS in B7 (ksi) 100 (HfS spec use hard coversions for columns 0 and E) 4 -9.65185657092471E.12 8 5 5.32766020834357E-I6 3 9 Ratm/Strass=A+B(T-TO)+C(T-T0)2+D(T-T0) 3+E(T-T0)A4+FT-T0)AI Term UTS 10 A B C D E F TO(F) 0 1 0 11 Enter Ry Constants 1 -3.18892E-04 -7.53276E-07 5.52257E-09 -9.65186E-12 5.32766E-15 69.8 1 -3.45977430697531E-04 12 Enter Rt Constants 1 -3.45977E-04 -5.95116E-08 1.98101E-09 -4.16385E-12 2.55615E-15 69.8 2 -5.95115601242924E-08 13 3 1.98100513770783E-09 14 4 -4.16385198889757E-12 15 5 2.55614659382911 E-1S 16 Cn 17 18 19 Temperature deg F 75 100 150 200 250 300 350 400 500 550 600 650 700 750 800 20 G')

21 Min YS Ratio, Ry 22 MinYS, SyRy (Y-1) ($B$7)*(C$21) 1.000 100.0 1.000 100.0 0.972 97.2 0.955 95.5 0.941 94.1 0.930 93.0 0.923 92.3 0.918 91.8 0.911 91.1 0.908 90.8 0.903 90.3 0.897 89.7 0.889 88.9 0.882 88.2 0.878 87.8 0

23 Min TS Ratio, Rt 1.000 1.000 0.973 0.957 0.943 0.931 0.921 0.911 0.893 0.883 0.873 0.862 0.851 0.841 0.834 2.4 Min TS. StRt ($B$6)*(C$23) 160.0 160.0 155.6 153.2 150.9 149.0 147.3 145.8 142.9 141.3 139.7 138.0 136.2 134.6 133.4 2T5 1.1Min TS., 1.lStRt (U) 1.1-(C24) 176.0 176.0 171.2 168.5 166.0 163.9 162.0 160.4 157.2 155.5 153.7 151.8 149.9 148.1 146.7 3 26 27 28 90.0 90.0 87.5 86.0 84.7 83.7 83.0 82.6 82.0 81.7 81.2 80.7 80.0 79.4 79.0 CD 29 0.9 SyRy 0.9(C22) 30 2/3 SyRy (2/3)'(C22) 66.7 66.7 64.8 63.7 62.7 62.0 61.5 61.2 60.7 60.5 60.2 59.8 59.3 58.8 58.5 53.3 53.3 53.3 53.3 53.3 CL 31 St/3 ($B$6)13 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 32 1.lStRt/3 1.1V(C24)Y3 58.7 58.7 57.1 56.2 55.3 54.6 54.0 53.5 52.4 51.8 51.2 50.6 50.0 49.4 48.9 .L..

373 2/3Sy (213)'$B$7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 66.7 34 00 35 36 37 38 CD 39 Design Stress - Hi (ksi) MIN(C$29,C$3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 52.4 51.8 51.2 50.6 50.0 49.4 48.9 C) 40 Design Stress - Lo (ksi) MIN(CS3O,CS3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 52.4 51.8 51.2 50.6 50.0 49.4 48.9 41- CD 42 43 2 6'"

44 Design Stress 0.85 - Hi (ksi) =0.85"C39 45.3 45.3 45.3 45.3 45.3 45.3 45.3 45.3 44.5 44.1 43.5 43.0 42.5 42.0 41.6 45 Design Stress 0.85 - Lo (ksi) =0.85*C40 45.3 45.3 45.3 45.3 45.3 45.3 45.3 45.3 44.5 44.1 43.5 43.0 42.5 42.0 41.6 0,.

-I 0)

Co CD

=r 0,

0) to 0 CD CwA

Section lID Table 2A,28 SI Metric Units Coefficients Term YS 0 I 0 1 -5.74005169897280E-04 Specifications (Enter size range hereM)(Enter size range hereXEnter size range here)

Type/Grade 2 -2.4406151979591 8E-06 Min TS in B6 (ksi) 1103.161499 Mettic is 585 IfCU speicthe soft conversion will appear in 56 3 3.22076337409858E-08 Min YS in B7 (ksi) 689.4758911 Metric is 415 IfCU spec:the soft conversion will appear in B7 4 -1.01321310213432E-10 1.00669738444055E-13 CD UTS Ratio/Stress=A+B(T-T0)-C (T-T0)A2+D(T-T0)-3+E(T-T0)14+F(T-T0)^5 A B C D E F TO (C)

Term 0

3 Enter Ry Constants 1 -5.74005E-04 -2.44062E-06 3.22076E-08 -1.01321E-10 1.00670E-13 21 -6.2275934560075E-04 Enter Rt Constants 1 -6.22759E-04 -1.92817E-07 1.15532E-08 -4.37104E-11 4.83001E-14 21 2 -1.92817436414203E-07 3 1.15532203104105E-08 4 -4.37104443015449E-11 5 4,83001165544386E-14 CD' Temperature dhg C 20 Min YS Ratio, Ry 1.000 1.000 0.972 0.952 0.940 0.930 0.923 0.918 0.915 0.912 0.909 0.906 0.901 0.895 0.888 0.882 0.878 0.878 -

MinYS, SyRy (Y-1) =($B$7)*(C$21 689 889 670.4 656.1 647.8 641.2 636.4 633.1 630.8 628.9 626.9 624.4 621.1 617.0 612.4 608.1 605.2 605.2 Min TS Ratio, Rt 1.000 1.000 0.973 0.954 0.942 0.931 0.921 0.913 0.904 0.896 0.888 0.879 0.870 0.860 0.850 0.841 0.834 0.831 Min TS, StRt =($B$6)*(C$23 1103.2 1103.2 10734 1052.1 1038.8 1026.9 1016.4 1006.8 997.7 988.7 979.4 969.6 959.2 948.4 937.7 927.8 920.2 916.5 G) 1.1Min TS., 1.1StRt (U) -1.1*(C24) 1213 1213 1180.8 1157.3 1142.6 1129.6 1118.0 1107.4 1097.4 1087.6 1077.4 1066.6 1055.2 1043.3 1031.4 1020.6 1012.2 1008.2 0.9 SyRy =0.9*(C22) 620.5 620.5 603.4 590.5 583.0 577.1 572.8 569.8 567.7 566.0 564.2 562.0 559.0 555.3 551.2 547.3 544.7 544.7 213SyRy =(2t3)*(C22) 459.7 459.7 447.0 437.4 431.8 427.5 424.3 422.1 420.5 419.2 417.9 416.3 414.1 411.3 408.3 405.4 403.5 403.5 StV3 =($8$6Yl3 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 367.7 1.1StRt/3 =1.1*(C24)/3 404.5 404.5 393.6 385.8 380.9 376.5 372.7 369.1 365.8 362.5 359.1 355.5 351.7 347.8 343.8 340.2 337.4 336.1 -

2/3Sy =(2/3)*$BS7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 459.7 CA FA, 3

337 336 T*

Design Stress - Hi MIN(C$29,C$3 368 368 368 368 368 368 368 368 366 363 359 356 352 348 344 340 337 336 3*

Design Stress - Lo MIN(C$30,C$3 368 368 368 368 368 368 368 368 366 363 359 356 352 348 344 340 CL.

CD "0

Design Stress 0.85 - Hi =0.85tC39 313 313 313 313 313 313 313 313 311 308 305 302 299 296 292 289 287 286 (D Design Stress 0.85 - Lo =0.85"C40 313 313 313 313 313 313 313 313 311 308 305 302 299 296 292 289 287 286 C (D

C" CLI,4 0

CD 00 cc 0 -4 Wo (CD

-41

CASE CASES OF ASME BOILER AND PRESSURE VESSEL CODE N-60-5 Approval Date: February 15, 1994 See Numeric Index for expiration and any reaffirmation dates.

Case N-60-5 Material for Core Support StructuresSection III, Division 1 Inquiry: What materials, in addition to those listed in Tables 2A, 2B, and 4,Section II, Part D, Subpart 1, may be used for core support structures constructed to the requirements of Subsection NG of Section III, Division 1?

Reply: It is the opinion of the Committee that the materials and stress intensity values listed in Table A may be used in the construction of core support structures in addition to those listed in Tables 2A, 2B and 4,Section II, Part D, Subpart 1. The following additional requirements shall be met.

(a) All other requirements of Subsection NG of Section III, Division 1, shall be met.

(b) Strain hardened SA-479 shall be identified with this Case number.

(c) Where welds are applied to strain hardened material, the stress intensity in the sections of the material where the temperatures during welding exceed 800'F shall not exceed values for annealed materials.

(d) Yield strength values are listed in Table B.

(e) Tensile strength values are listed in Table C.

W/Chemical composition for Ni-Cr-Fe ASTM B 637 Types 1 and 2 is listed in Table D.

(g) Heat treatments for Ni-Cr-Fe ASTM B 637 Types 1 and i are listed in Table E.

-and Grade 718 Type 2 (h) Room temperature mechanical properties for Ni-Cr-Fe ASTM B 637 Types 1 and 2iare listed in Table F.

_____and Grade 718 Type 2 Page 36/44

zo TABLE A OFrn Stress Intensity, Kips/sq in.

Min. for Metal Temperature, Type Min. UIt. *F, Not to Exceed Nominal P Prod. Spec. or Yield Tens.

Composition No. Form No. Grade Notes Str. Str. 100 200 300 400 500 600 650 700 750 800 CL 13Cr 6 Plate SA-240 TP-410 30.0 60.0 20.0 18.4 17.7 17.4 17.2 16.8 16.5 16.2 15.7 15.1 22Cr-13Ni-5Mn ... Plate SA-240 XM-19 7,8 55.0 100.0 33.3 33.2 31.4 30.2 29.7 29.2 29.0 28.8 28.5 28.2 22Cr-13Ni-5Mn ... Bar A 479-74 XM-19 7,8 55.0 100.0 33.3 33.2 31.4 30.2 29.7 29.2 29.0 28.8 28.5 28.2 18Cr-8Ni 16Cr-12Ni-2Mo 18Cr-10Ni-Ti 8

8 8

FFBS FFBS FFBS SA-193 SA-193 SA-193 88 B8M B8T 7

7 7

30.0 30.0 30.0 75.0 75.0 75.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 18.7 19.2 19.2 17.4 17.9 17.9 16.4 17.0 17.0 16.1 16.6 16.6 15.9 16.3 16.3 15.5 16.0 16.0 15.1 15.8 15.8 i

0 18Cr-lONi-Cb 8 FFBS SA-193 B8C 7 30.0 75.0 20.0 20.0 20.0 20.0 19.9 19.3 18.9 18.6 18.4 18.3 26Ni-15Cr-2Ti ... FFBS SA-453 660 5,7 85.0 130.0 43.3 43.3 43.3 43.3 43.3 43.3 43.3 43.3 43.3 42.6 15.1 0 18Cr-8Ni 8 SmIs Tube A 511-71 MT304 6,7 30 75 20.0 20.0 20.0 18.7 17.4 16.4 16.1 15.9 15.5 t* 18Cr-8Ni 8 Smis Tube A 511-71 MT304L 6,7 25 70 16.6 16.6 16.6 15.7 14.7 13.9 13.7 13.4 13.2 13.0 16Cr-12Ni-2Mo 8 Smls Tube A 511-71 MT316 6,7 30 75 20.0 20.0 20.0 19.2 17.9 17.0 16.6 16.3 16.0 15.8 16Cr-12Ni-2Mo 8 SmIs Tube A 511-71 MT316L 6,7 25 70 16.6 16.6 16.6 15.5 14.4 13.5 13.2 12.8 12.6 12.3 18Cr-8Ni 8 Weld Tube A 554-72 MT304 6,7 30 75 20.0 20.0 20.0 18.7 17.4 16.4 16.1 15.9 15.5 15.1 18Cr-8Ni 8 Weld Tube A 554-72 MT304L 6,7 25.0 70.0 16.6 16.6 16.6 15.7 14.7 13.9 13.7 13.4 13.2 13.0 16Cr-12Ni-2MVlo 8 Weld Tube A 554-72 MT316 -6,7 30 75 20.0 20.0 20.0 19.2 17.9 17.0 16.6 16.3 16.0 15.8 16Cr-12Ni-2Mo 8 Weld Tube A 554-72 MT316L 6,7 25.0 70.0 16.6 16.6 16.6 15.5 14.4 13.5 13.2 12.8 12.6 12.3 Ni-Cr-Fe ... FFBS SB-637 688 9 40 100 26.7 26.1 25.5 25.1 24.6 24.3 24.1 24.0 23.9 23.8 Ni-Cr-Fe ... FFBS .SB-637 688 5,10 90 140 46.7 46.7 46.7 46.7 46.7 46.7 46.7 46.7 46.7 46.5 Ni-Cr-Fe ... FFBS SB-637 688 5,11 115 170 56.7 56.7 56.7 56.7 56.7 56.7 56.7 56.7 56.7 56.5 Ni-Cr-Fe ... FFBS S B-637 688 5,12 100 160 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.1 0 Ni-Cr-Fe 43 Plate SB-168 ... 15 35 80 23.3 23.2 23.3 23.3 23.3 23.3 23.3 23.3 23.3 23.3 Ni-Cr-Fe ... FFBS B 637 TP-1 5 100 160 53.3 53.3 53.3 53.3 53.3 53.2 52.7 52.1 51.5 ...

Ni-Cr-Fe ... FFBS B 637 TP-2 5 85 150 50.0 50.0 50.0 50.0 50.0 50.0 50.0 50.0 50.0 16Cr-12Ni-2Mo 8 FFBS SA-479 316 1,2,7,13 60 85 28.3 28.3 26.8 25.9 25.7 25.7 25.7 25.7 25.7 25.4 16Cr-12Ni-2Mo 8 FFBS SA-479 316 1,2,7,14 65 85 28.3 28.3 26.8 25.9 25.7 25.7. 25.7 25.7 25.7 25.4 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,7 50 90 30.0 30.0 28.3 27.4 26.8 26.4 26.1 25.7 25.2 24.6 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,7 65 90 31.6 31.6 29.9 29.0 28.7 28.7 28.7 28.7 28.7 28.4 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,3,5,7 80 100 33.3 33.3 31.5 30.5 30.2 30.2 30.2 30.2 30.2 29.9 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,4,5,7 95 110 36.6 36.6 34.6 33.5 33.3 33.3 33.3 33.3 33.3 32.8

IABLE A (CUNT'D)

NOTES:

(1) ' Strain hardened. (The tensile properties for these items shall meet the minimum specified. These materials shall conform to all other requirements of the referenced specification. Surface hardness as shown in SA-479 is not required.)

(2) Yield strength values are listed in Table B.

(3) Maximum.tensile strength--140,O00 psi, (4) Maximum tensile strength--150,O00 psi.

(5) The designer shall consider the effects of temperature and environment on the material properties of precipitation hardening alloys and cold worked austenitic stainless steels.

(6) Supplementary requirement S-2 for tensile testing of the specification is mandatory.

(7) At temperatures above 100*F, the design stress intensity values may exceed 662/% and may also reach 90% of the yield strength (0.2% offset) at temperature. This may result in a >

permanent strain of as much as 0.1%. When this amount of deformation is not acceptable, the designer should reduce the design stress intensity to obtain an acceptable deformation.

Section III, Division 1, Table 1-2.4 lists multiplying factors which, when applied to the yield strength values shown on Table 1-2.2, will give a design stress intensity that will result in lower levels of permanent strain.

(8) The S value5 for Type XM-19 stainless steels vary with the annealing temperature (see. Tab 1B).

(9) Solution heat treated.

(10) Type 1.

(11) Type 2.

(12) Type 3.

(13) Over 2 in.

(14) Up to and including 2 in.

(15) Hot finished.

qM CA Z2 zg0 I m "IS (J1,o

TABLE B Yield Strength, Kipslsq in. OZr Yield Strength Values Sy for Metal Temperature V)

Type Spec. *F, Not to Exceed u1M Nominal Prod. or Min.

Composition Form Spec. No. Grade Notes Yield 100 200 300 400 500 600 650 700 750 800 18Cr-8Ni Smis Tube A 511-71 MT304 ... 30.0 30.0 25.0 22.5 20-7 19.4 18.2 17.9 17.7 17.3 16.8 18Cr-8Ni Smis Tube A 511-71 MT304L ... 25.0 25.0 21.3 19.1 17.5 - 16.3 15.5 15.2 14.9 14.7 14.4 16Cr-12Ni-2Mo SmIs Tube A 511-71 MT316 ... 30.0 30.0 25.8 23.3 21.4 19.9 18.8 18.5 18.1 17.8 17.6 16Cr-12Ni-2-Mo Smis Tube A 511-71 MT316L ... 25.0 25.0 21.1 18.9 17.2 15.4 15.0 14.6 14.3 14.0 13.7 1l8Cr-8Ni Wld Tube A 554-72 MT304 ... 30.0 30.0 25.0 22.5 20.7 19.4 18.2 17.9 17.7 17.3 16.8 18Cr-8Ni Wld Tube A 554-72 MT304L ... 25.0 25.0 21.3 19.1 17.5 16.3 15.5 15.2 14.9 14.7 14.4 16Cr-12Ni-2Mo Wid Tube A 554-72 MT316 ... 30.0 30.0 25.8 23.3 21.4 19.9 18.8 18.5 18.1 17.8 17.6 16Cr-12Ni-2Mo Wld Tube A 554-72 MT316L ... 25.0 25.0 21.2 18.9 17.2 15.9 15.0 14.6 14.3 14.0 13.7 Ni-Cr-Fe FFBS SB-637 688 3 40.0 40.0 39.1 38.3 37.6 36.9 36.4 36.2 36.0 35.9 35.7 Ni-Cr-Fe FFBS SB-637 688 4 90.0 90.0 87.7 86.4 85.3 84.5 84.1 83.9 83.8 83.7 83.6 Ni-Cr-Fe FFBS S B-637 688 5 115.0 115.0 112.0 110.2 109.0 108.0 107.5 107.2 107.0 106.9 106.8 Ni-Cr-Fe FFBS S B-637 688 6 100.0 100.0 99.0 95.2 94.0 93.1 92.5 92.2 92.0 91.9 91.8 Ni-Cr-Fe FFBS B 637 TP-1 100.0 100.0 97.1 95.2 93.4 92.0 90.0 90.4 90.1 89.9 Ni-Cr-Fe FFBS B 637 TP-2. ... 85.0 85.0 82.4 81.2 80.4 79.9 79.8 79.8 79.8 79.8 16Cr-12Ni-2Mo FFBS SA-479 316 7 60.0 60.0 55.1 52.1 49.8 48.3 47.5 47.0 46.3 45.4 44.5 16Cr-12Ni-2Mo FFBS SA-479 316 8 65.0 65.0 59.8 56.5 54.0 52.3 51.4 50.9 50.1 49.1 48.1 Ni-Cr-Fe Plate SB-168 9 35.0 35.0 32.7 31.0 29.8 28.8 27.9 27.4 27.0 26.5 26.1 16Cr-12Ni-2Mo FFBS SA-193 B8M 50.0 50.0 46.0 43.5 41.5 40.3 39.6 39.2 38.6 37.8 37.0 16Cr-12 Ni-2Mo FFBS SA-193 B8M 65.0 65.0 59.8 56.5 54.0 52.3 51.4 50.9 50.1 49.1 48.1 16Cr-12Ni-2Mo FFBS SA-193 B8M 80.0 80.0 73.5 69.6 56.5 64.5 53.3 62.6 61.8 60.5 59.0 16Cr-12Ni-2Mo FFBS SA-193 B8M 95.0 95.0 87.5 82.6 78.9 76.5 75.1 74.4 73.3 71.9 70.5 22Cr-13Ni-5Mn Plate SA-240 XM-19 1 55.0 55.0 47.0 43.4 40.8 38.8 37.3 36.8 36.3 35.8 35.3 22Cr-13Ni-5Mn Bar A 479-74 XM-19 1 55.0 55.0 47.0 43.4 40.8 38.8 37.3 36.8 36.3 35.8 35.3 22Cr-13Ni-5Mn Plate SA-240 XM-19 2 55.0 55.0 44.6 39.3 35.7 33.3 32.0 31.5 31.4 31.2 31.1 22Cr-13Ni-5Mn Bar A 479-74 XM-19 2 55.0 55.0 44.6 39.3 35.7 33.3 32.0 31.5 31.4 31.2 31.1 NOTES:

(1) For material annealed at 1925-1975-F.

(2) For material annealed at 2025-2075'F.

(3) Solution heat treated.

(4) Type 1.

(5) Type 2. ,~

(6) Type 3.

(7) Over 2 in.

(8) Up to and including 2 in.

(9) Hot finished.

CASE (continued)

CASES OF ASME BOILER AND PRESSURE VESSEL CODE N-60-5 ise.tC .S-ec TABLE C MATERIALS PROPERTIES, SUBSECTION NG TENSILE STRENGTHS, S Tensile Strength Values, S,, for Austenitic Steel and High Nickel Alloys for Class 1 Components Spec. Temperature, *F Nominal Prod. Spec. Type or M.n.

Composition Form No. Grade T.S. 100 200 300 400 500 600 650 700 750 800 18Cr-8Ni FFBS SA-193 88 75.0 75.0 70.9 66.0 64.3 63.5 63.5 63.5 63.5 63.2 62.6 16Cr-12N]-2Mo FFBS SA-193 B8M 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.5 71.0 18Cr-1ONI-Ti FFBS SA-193 B8T 75.0 75.0 73.4 67.3 68.5 68.5 68.5 68.5 68.5 68.5 68.5 18Cr-iONI-Cb FFBS SA-193 B8C 75.0 75.0 71.8 66.0 61.9 60.2 59.4 58.9 58.5 58.5 58.5 26Ni-15Cr-2TI FFBS SA-453 660 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 18Cr-8NI SmIs. Tube A 511 MT304 75.0 75.0 70.9 66.0 64.3 63.5 63.5 63.5 63.5 63.2 62.6 18Cr-8NI SmIs. Tube A 511 MT304L 70.0 70.0 66.2 60.8 58.5 57.7 57.0 56.6 56.2 55.8 55.4 16Cr-12NI-2Mo Smls. Tube A 511 MT316 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.5 71.0 16Cr-12 NI-2 Mo SmIs. Tube A 511 MT316L 70.0 70.0 67.7 63.9 62.4 61.6 61.6 61.6 61.6 61.2 60.8 18Cr-8NI Wld. Tube A 554 MT304 75.0 75.0 70.9 66.0 64.3 63.5 63.5 63.5 63.5 63.2 62.6 16Cr-12Ni-2Mo Wid. Tube A 554 MT316 75.0 75.0 75.0 73.4 71.8 71.8 71.8. 71.8 71.8 71.5 71.0 NI-Cr-Fe FFBS SB-637 Solu. 100.0 100.0 100.0 100.0 100.0 100.0 99.4 98.8 98.5 98.2 98.0 Treated 68 8 NI-Cr-Fe FFBS SB-637 Type 1 688 140.0 140.0 140.0 140.0 140.0 140.0 140.0 140.0 140.0 140.0 139.8 NI-Cr-Fe FFBS S B-637 Type 2 688 170.0 170.0 170.0 170.0 170.0 170.0 170.0 170.0 170.0 170.0 169.8 Ni-Cr-Fe FFBS SB-637 Type 3 688 160.0 160.0 160.0 160.0 160.0 160.0 160.0 160.0 160.0 160.0 159.2 Ni-Cr-Fe FFB5 B 637 1Type1 160.0 160.0 156.4 152.7 150.2 147.8 145.2 143.8 142.2 140.4 ...

Nl-Cr-Fe FFBS B 637 Type 2 150.0 150.0 147.2 145.5 144.0 142.5 140.9 140.0 139.1 138.7 ...

16Cr-12N[-2Mo FFBS SA-479 316 85.0 85.0 85.0 80.3 77.6 77.1 77.1 77.1 77.1 77.1 76.3 16Cr-12Ni-2Mo FFBS SA-193 B8M 90.0 90.0 90.0 85.1 82.4 81.6 81.6 81.6 81.6 81.6 80.9 16Cr-12Ni-2Mo FFBS SA-193 88M 100.0 100.0 100.0 94.6 91.5 90.8 90.8 90.8 90.8 90.8 89.6 16Cr-12Ni-2Mo FFBS SA-193 B8M 110.0 110.0 110.0 104.0 100.7 99.9 99.9 99.9 99.9 99.9 98.6 13Cr Plate SA-240 410 60.0 60.0 60.0 58.9 57.7 56.9 55.4 54.5 53.0 51.3 49.1 16Cr-12NI-2Mo Wid. Tube A 554 MT316L 70.0 70.0 67.7 63.9 62.4 61.6 61.6 61.6 61.6 61.2 60.3 18Cr-8NI Wld. Tube A 554 MT304L 70.0 70.0 66.2 60.8 58.5 57.7 57.0 56.6 56.2 55.8 55.0 15Cr-26Ni-2TI FFBS SA-638 660 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130,0 130.0 130.0 18Cr-iONi-Cb FFBS SA-182 F347 75.0 75.0 71.8 66.0 61.7 60.2 59.4 58.9 58.5 58.5 58.5 18Cr-8NI FFBS SA-479 304 75.0 75.0 71.0 66.0 64.3 63.5 63.5 63.5 63.5 63.1 62.6 16Cr-12NI-2Mo FFBS SA-479 316 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.4 70.9 18Cr-1ONi-Cb FFBS SA-479 347 75.0 75.0 71.8 66.0 61.9 60.2 59.4 58.9 58.5 58.5 58.5 18Cr-8Ni FFBS SA-479 304L 70.0 70.0 66.2 60.8 58.5 57.7 57.0 56.6 56.2 55.8 55.4 16Cr-12NI-2Mo FFBS SA-479 316L 70.0 70.0 67.9 63.9 62.4 61.6 61.6 61.6 61.6 61.2 60.8 18Cr-8NI Nuts SA-194 8 75.0 75.0 71.0 66.0 64.3 63.5 63.5 63.5 63.5 63.1 62.6 18Cr-iONI-Cb Nuts SA-194 8C 75.0 75.0 71.8 66.0 61.9 60.2 59.4 58.9 58.5 58.5 58.5 16Cr-12NI-2Mo Nuts SA-194 8M 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.4 70.9 22Cr-13Ni-SMn Plate SA-240 XM-19 100.0 100.0 99.5 94.3 90.7 89.1 87.8 87.1 86.5 85.7 84.8 22Cr-13NI-5Mn Bar A 479-74 XM-19 100.0 100.0 99.5 94.3 90.7 89.1 87.8 87.1 86.5 85.7 84.8 GENERAL NOTE: The tabulated values of tensile strength and yield strength are those which the Committee believes are suitable for use in

-design calculations required by this Case. At temperatures above room temperature the values of tensile strength tend toward an average or expected value which may be as much as 10% above the tensile strength trend curve adjusted to the minimum specified room temperature tensile strength. At temperatures above room temperature the yield strength values correspond to the yield strength trend curve adjusted to the minimum specified room temperature yield strength. Neither the tensile strength nor the yield strength values correspond exactly to either averageor minimum as these terms are applied to a statistical treatment of a homogeneous set of data. Neither the ASME Material Specifications nor the rules of this Section require elevated temperature testing for tensile or yield strengths of production material for use In Code components. It Is not intended that results of such tests, If performed, be compared with these tabulated tensile and yield strength values for AS ME Code acceptance/rejection purposes for materials. If some elevated temperature tests results on production material are lower than these tabulated values by a large amount (more than the typical variability of material and suggesting the possibility of some error) further Investigation by retest or other means should be considered.

5 (N-60-S)

Page 40/44

CASE (continued) TABLE D ASTM B 637 TYPES 1 AND 2 N-60-5 CHEMICAL REQUIREMENTS Element Percent Carbon 0.020 - 0.060 Manganese 1.00 max Silicon 0.50 max Phosphorus 0.008 max Sulfur 0.003 max Chromium 14.50 - 17.00 Cobalt 0.050 max Columbium +

Tantalum 0.70- 1.20 Titanium 2.25 - 2.75 Alumunium 0.40- 1.00 Boron 0.007 max Iron 5.00 - 9.00 Copper 0.50 max Zirconium 0.050 max Vanadium 0.10 max Nickel 70.00 min TABLE E ASTM B 637 HEAT TREATMENT Solution Annealing Precipitation Hardening Type 1 1975°F +/- 25°F, hold 1 13201F +/- 251F, hold 20 h, +2 to 2 h, cool by water or oil -0 h, air cool quenching Type 2 1975 0 F +/- 25 0F, hold 1 1400°F +/- 25°F, hold 100 h, +4 to 2 h, cool by water or oil -0 h, air cool quenching Grade 718 Type 2 1850' to 1922°F, hold 1 to 2 h, cool by water or oil quenching 1300'F +/-15'F, hold 6 h

+lh -0 min., air cool Wi r AAA U-A+

TABLE F ASTM B 637 MECHANICAL PROPERTIES (Minimum Room Temperature)

Property Yield strength psi Tensile strength psi Type 1 100,000 160,000 Type 2 85,000 150,000 Grade 718 Type 2 100,000 160,000 vI Elongation in 2 in. % 20 20 20 Reduction of area % 20 20 20 Hardness 267-363 HB 267-363 HBW 27-40 RC 27-40 HRC Page 41/44

0*

FFBS-Fittings, Forgings, Bars, Shapes N,

Modified 718 Data Analysis Worksheet C&S Item #10-1516 NMDA_2011_03_25-Mod7l8 050711.xlsm Chemical Composition for Three Heats of Material Page 1 of 2

1. Comi)onents + 14 _ _ 1 I 1 I I

+/- f __

F I.')

Component Balance Nom Min Max C - I II 0 i i -9.999999E-C ENo 1 01 0.081 Si LNo 1 01 0.35 i ,I Mn LNo 1 01 0.351 Si I 3 P No 0 0.0151 0 0.4 S iNo 0 0.1 5 Ni No 50 55 Mn Cr No +/-

17 1-21 0 I .I 0.4 Fe Yes Mo No 2.8 3.3 P I II I

,I . I A] F No +/-

0.2 1- 0.81

-- I-I 0 0.02 Ti No 0.65 1.15 I Nb B

INo No I 4.751 0

5.51 0.006 S

0 El

__ I 0.02 K I.

Co iNo 0 1 Ni wD I I I 50 58 _

m m _Cr 17 22

_______ 1 ___

_Fe I I :I 1 1I 1 1 1 I -

i -

+ .~-I Mo Mo 2.6 3. 4

+ +/-

I Al m 0.2 1 j.I Ti _ -

-II I I7 I 0.6 1.4 p _ 7 Nb Z 4.6 5.6 __

I Ole 4P

+ + + +/- 0 0.008 _

-0

_ _ ______ ___ ___ ___ ___ __ ___ _ Co___ 0 ___ ___ 1.

1.5 CD WA Page 1 NMDA_2011_03_25-Mod7l8 050711.xlsm

Modified 718 Data Analysis Worksheet C&S Item #10-1516 NMDA_2011_03_25-Mod718 050711.xlsm Chemical Composition for Three Heats of Material Page 2 of 2 Number of Heats CHEMISTRY HEAT ID LOT C Si Mn P S Ni Cr Fe Mo Al Ti Nb B Co A 0.03 0.1 0.04 0.004 0.0003 52.41 18.59 0 3.07 0.52 0.94 5.12 0.0048 0.03 B 0.03 0.08 0.04 0.004 0.0002 52.49 18.65 0 3.08 0.55 0.95 5.07 0.0038 0.03 C 0.03 0.06 0.04 0.004 0.0001 52.34 18.65 0 3.09 0.54 0.96 5.11 0.0042 0.03 Page NMDA_2011_03_25-Mod7l8 050711.xlsm

ENCLOSURE 4 SMV-2011-000034-NP, REVISION 0 TOSHIBA ENGINEERING REPORT JET PUMP BEAM FABRICATION - COMPARISON OF MODIFIED ALLOY 718 AND ALLOY X-750 MATERIALS (Non-Proprietary)

Nine Mile Point Nuclear Station, LLC December 30, 2011

PSNE Control Number: WEC-2011-000199 This report contains the non-proprietary information that is included in the proprietary version of this report. I Westinghouse Document Number TR-MODS-1 1-4-NP The proprietary version of this report contains proprietary information that is the intellectual property of TOSHIBA. Accordingly, the proprietary report is available only under license from TOSHIBA and may not be reproduced or disclosed, wholly or in part, by any license to any other person or organization.

TOSHIBA CORPORATION NUCLEAR ENERGY SYSTEMS & SERVICES DIVISION Toshiba Engineering Report Jet Pump Beam Fabrication -

Comparison of Modified Alloy 718 and Alloy X-750 Materials Rev. Initial Issue Date Issued by Approved by Reviewed by Prepared by Summary TOSHIBA CORPORATION Nuclear Energy Systems & Services Division

TABLE OF CONTENTS 1 IN T ROD U C TION ........................................................................................................................... 1 2 JET PUMP BEAM ASSEMBLY .................................................................................................. 1 2.1 B A C K GRO U N D ............................................................................................................................. 1 2.2 MATERIAL OPTIMIZATION OF MODIFIED ALLOY 718 ..................................................... 2 2.3 MANUFACTURING PROCESS OF MODIFIED ALLOY 718 JET-PUMP BEAM ................. 3 2.4 MATERIAL PROPERTIES ..................................................................................................... 4 2.5 CHEMICAL COMPOSITION .................................................................................................... 8 2.6 MODIFIED HEAT TREATMENT .............................................................................................. 8 2.7 M ECH AN ICA L PRO PERTY ........................................................................................................ 10 2.8 SCC SUSCEPTIBILITY IN HIGH AND LOW TEMPERATURE WATER ............................. 15 2.9 GRAIN BOUNDARY ANALYSIS ............................................................................................ 17 2.10 LONG-TERM CONSTANT LOAD TEST ................................................................................ 18 2.11 REQUIRED TESTS IN BWRVIP-84 AND BWRVIP- 138 ....................................................... 19 2.12 FATIGU E PRO PERTY .................................................................................................................. 23 2.13 RADIATION RELAXATION RATE ....................................................................................... 24 2.14 SPRING PROPERTY OF JET-PUMP BEAM ........................................................................... 26 2.15

SUMMARY

OF MATERIAL PROPERTY TESTS AS RELATED TO JP BEAMS ................ 27 3 RE FER EN C E S .............................................................................................................................. 28 ATTACHMENT 1 - CROSS REFERENCE TABLE - VIP84 RI REQUIREMENTS FOR X-750 VS. FABRICATION METHODS UTILIZED FOR ALLOY 718 JP BEAM ATTACHMENT 2 - CODE CASE 60-N-6 SMV-2011-000034-NP Rev.0

1 INTRODUCTION Westinghouse / Toshiba are supplying Constellation Energy Nuclear Group (CENG) with 20 new jet pump (JP) beams to replace the ones currently installed at Nine Mile Point Unit 2 (NMP2). The installed jet pump beams are a General Electric design, and are fabricated from alloy X-750 material. This choice of material, along with stresses inherent to the design of the beam, makes the beam susceptible to premature failure. The new beams to be installed by Westinghouse are a Toshiba design, and they are fabricated from modified heat treatment alloy 718 material. Note that the adjective "Modified" refers to the modified heat treatment for this particular alloy. For simplicity, the term Modified Alloy 718 will be used hereafter in this document to identify this material. This report compares the structural properties of both materials, and demonstrates the superiority of alloy 718 over alloy X-750. The requirements of BWR VIP-84 are also factored in to this comparison (Attachment 1).

2 JET PUMP BEAM ASSEMBLY Jet pump beams are located at the top of the inlet mixer assembly and are used to seat and mechanically lock the inlet mixer to the riser pipe transition piece. The jet pump beam is deflected during installation to provide an axial preload of approximately 25,000 pounds on the corresponding jet pump. It is hydraulically deflected while in place above the jet pump assembly, and is fixed in the preloaded condition via a bolt that is integral to the jet pump beam assembly. The bolt is threaded through the jet pump beam and contacts the top of the jet pump. After contact, the bolt is loaded to a predetermined torque value through a given angular rotation. An iterative process is used and both the torque and the rotation are monitored to verify that the jet pump beam and inlet mixer are properly seated. After the beam is tensioned, an integral locking device engages around the bolt and prevents it from loosening.

This in turn prevents the beam from losing preload during reactor operation.

2.1 BACKGROUND

The OEM jet pump beam material was fabricated from alloy X-750. Although stress corrosion cracking (SCC) susceptibility of alloy X-750 was improved by modified heat treatment, SCC failures of alloy X-750 jet pump beams have occurred in BWR plants. The material chosen, along with the geometry of the beam, makes the OEM beam susceptible to premature failure.

The Toshiba-designed jet pump beams being installed at NMP2 (Figure 2-1) are an improvement over the existing beam design. Toshiba has developed a modified alloy 718 which has greater material reliability than alloy X-750. Compared to X-750, the modified alloy 718 beam has greater SCC resistance, higher ductility, and superior fatigue and spring properties. Its high strength and hardness is similar to that of X-750, allowing it to meet the requirements of bolting materials. In addition, Toshiba adjusted the beam geometry to minimize stresses under the preloaded condition. The combination of material choice and geometry improvements reduce the Toshiba beam's susceptibility to IGSCC.

Alloy 718 was selected as an alternative material to X-750 and alloy 725 for the following reasons;

1. Superior material properties such as corrosion resistance as compared to X-750.

SMV-2011-000034-NP Rev.0

2

2. Higher manufacturability for various product forms such as plate, strip, bar, wire, and forging, than alloy 725 (normally alloy 725 is applicable for bar, strip and pipe).

3. Alloy 718 has been widely used in jet engines, gas turbines, aerospace and nuclear fuel with established manufacturing process. On the other hand, alloy 725 has not been widely used for industry application. In addition to the standard 718 specification, modified heat treatment conditions have been developed to improve SCC resistance and to provide similar mechanical strength to X-750. Toshiba believes that modified alloy 718 has excellent material properties based upon the results of testing.

Alloy 725 would be considered as a possible alternative to alloy X-750, but alloy 725 has not been widely used for industrial applications. Because alloy 718 has a proven in-service record, it was deemed a more prudent choice.

Content Deleted -

Toshiba Proprietary Information Figure 2-1 Modified Alloy 718 Jet Pump Beam 2.2 MATERIAL OPTIMIZATION OF MODIFIED ALLOY 718 The Toshiba modified alloy 718 has the following material optimization:

• Higher resistance to SCC initiation compared to alloy X-750 Higher resistance to low temperature SCC compared to alloy X-750 (Requirement of EPRI BWRVIP-84)

SMV-20 11-000034-NP Rev.0

3 0 Higher resistance to SCC crack growth compared to alloy X-750 (Requirement of EPRI BWRVIP-138)

• Similar strength and hardness compared to alloy X-750

• Higher ductility compared to alloy X-750 0 Superior fatigue and spring properties compared to alloy X-750

• Similar irradiation relaxation rate compared to alloy X-750 2.3 MANUFACTURING PROCESS OF MODIFIED ALLOY 718 JET-PUMP BEAM The Toshiba manufacturing process for the modified alloy 718 jet pump beam is shown in Figure 2-2. Remelt processes such as vacuum induction melt (VIM) and vacuum arc remelt (VAR) are applied to the modified alloy 718 jet pump beam. 6-phase formed during hot forming can be solutionized by solution heat treatment at 1030'C (1886°F). There is no difference in the manufacturing process between modified alloy 718 and alloy X-750 Jet-Pump Beams except for heat treatment conditions.

Grain size can be controlled within a range of No.3 to No. 5 (ASTM grain size number).

Content Deleted -

Toshiba Proprietary Information Figure 2-2 Manufacturing Process of Modified Alloy 718 Jet-Pump Beam SMV-2011-000034-NP Rev.0

4 2.4 MATERIAL PROPERTIES Table 2-1 shows the evaluation program for material properties of modified alloy 718 compared to alloy X-750. Several tests from many heats of material were conducted to evaluate material properties of modified alloy 718. Table 2-2 shows the chemical composition of the test materials, and Table 2-3 shows the heat treatment condition of the test materials.

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5 Table 2-1 Beam Evaluation Program Content Deleted -

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6 Table 2-2 Chemical Compositions of Test Materials I Content Deleted -

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7 Table 2-3 Heat Treatment Condition of Test Materials Content Deleted -

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8 2.5 CHEMICAL COMPOSITION The chemical composition of modified alloy 718 shall be in accordance with Table 2-4. The chemical composition of modified alloy 718 is the same as that of conventional alloy 718 specified with ASME SB-637 alloy UNS N07718.

Table 2-4 Chemical Composition for Alloy 718 (%)

ASME SB-637 C Si Mn P S Ni Cr Fe* Mo Cu AI Ti Nb+Ta B Co Alloy 718 170- 280-

.500- 020- 0.65- 4.75-5.50 <0.006 <0.25

<0.08 <0.35 <_.0.35 <0.015 <0.015 Remainder <0.30 (UNS N07718) - 55.0 21.0 3.30 0.80 1.15 The element shall be determined arithmetically by difference.

2.6 MODIFIED HEAT TREATMENT Solution heat treatment (SHT) for modified alloy 718 shall be 1850°F-1922°F (1010°C-1050°C),

target temperature of 1886°F (1030'C), for 1 to 2 hours2.314815e-5 days <br />5.555556e-4 hours <br />3.306878e-6 weeks <br />7.61e-7 months <br />, followed by rapid quenching in oil or water.

SHT for modified alloy 718 shall be followed by precipitation hardening heat treatment at 1300 0Fd15 0 F (704°C+8°C) for 6 hours6.944444e-5 days <br />0.00167 hours <br />9.920635e-6 weeks <br />2.283e-6 months <br />, +1 -0 hours, followed by air cooling. Solution and precipitation hardening heat treatment conditions were determined from the T-T-P (time-temperature-precipitation) curve (Reference 3 and Figure 2-3) and isothermal aging curves for yield strength and elongation of alloy 718 (Figure 2-4). In order to improve SCC resistance and ductility, SHT temperature 1010-1050'C was selected for complete solution and the precipitation hardening heat treatment condition 704°C/6 hours was selected to avoid the precipitation of 6-phase from Figure 2-3, which are more than 101,526 psi (700 MPa) in yield strength and 30% in elongation, for altemative material to alloy X-750, are given by the precipitation hardening heat treatment condition of 704'C/6 hours from Figure 2-4.

For application of modified alloy 718 for the jet pump beam, the yield strength of modified alloy 718 is similar to that of alloy X-750 by the selection of 704'C (1300'F)/6 h as the aging condition. As a result, elongation of modified alloy 718 is much higher than that of alloy X-750.

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9 1010-1050°C (1850-1922- F) 1030-C (1886- (18}6 F) oooF)- -_-_-

-- ....- - - -- I o1,ohomv

• • e NI.N*

Nrh~ i sAI MbI T C Id M.C 900*

800-" ' '

7w -

i 10 *X I I Ii 600 500to Ageing Time (Hr)

Figure 2-3 T-T-P Diagram for Alloy 718 (Reference 3) 100

,704 (13 F)(

so---.-- -- -- - o - 0

( 60 0

>40 40 60 - I 620"C 40 ------- - 650*c 20, C--T0o -- 300 F)I 010 20 50 100 1

qing Time, hr Figure 2-4 Aging Condition Dependency for Yield Strength and Elongation of Alloy 718 (Reference 3)

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10 2.7 MECHANICAL PROPERTY Figure 2-5 shows yield strength and Figure 2-6 shows tensile strength of modified alloy 718 compared to alloy X-750. Figure 2-7 shows elongation and Figure 2-8 shows reduction of area of modified alloy 718 compared to alloy X-750. Yield strength, tensile strength, elongation and reduction of area of modified alloy 718 are satisfied with minimum requirement of alloy X-750 (UNS N07750 (Grade 688)) Type 3 specified in ASME/ASTM SB-637/B637. Modified alloy 718 has similar strength and higher ductility compared to alloy X-750. Figure 2-9, Figure 2-10, and Figure 2-11, respectively, show yield strength, tensile strength and elongation of cold rolled and aged modified alloy 718, conventional alloy 718 and alloy X-750 (Reference 3). Yield strength and tensile strength of modified alloy 718 are similar to those of alloy X-750 in the all of the range of cold roll reduction ratio. Elongation of modified alloy 718 is very excellent and higher than that of alloy X-750 in the range of 0 to 30% cold roll reduction ratio. Figure 2-12 shows hardness of modified alloy 718 compared to alloy X-750. Hardness of modified alloy 718 is satisfied with requirement of alloy X-750 (UNS N07750 (Grade 688)) Type 3 specified in ASME/ASTM SB-637/B637. Modified alloy 718 has similar hardness compared to alloy X-750.

Content Deleted -

Toshiba Proprietary Information Figure 2-5 Yield Strength of Modified Alloy 718 Compared to Alloy X-750 SMV-2011-000034-NP Rev.0

11 Content Deleted -

Toshiba Proprietary Information Figure 2-6 Tensile Strength of Modified Alloy 718 Compared to Alloy X-750 Content Deleted -

Toshiba Proprietary Information Figure 2-7 Elongation of Modified Alloy 718 Compared to Alloy X-750 SMV-2011-000034-NP Rev.0

12 Content Deleted -

Toshiba Proprietary Information Figure 2-8 Reduction of Area of Modified Alloy 718 Compared to Alloy X-750 150 E

E t Ji) n 100k LJ2)

>- c t RE2) 30 40 50 60 70 C.W %

Figure 2-9 Yield Strength of Cold Rolled and Aged Modified Alloy 718, Conventional Alloy 718 and Alloy X-750 (Reference 3)

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13

.- A" ..0.*

E 150- -.0

--- o SAlloy Heat Treatment "A2n 10 ModifiedAIIoy 718 1010°/1lh+CW+704°C/6h (Heat JA)

C A ConvenfionalAloy 718 1010DC/1h+CW+718*CISh-621 G/8h (Heat J2) 02 1)0 LII Alloy X-75U 11093 C/1hvv-+7('010h (Heat RE2) 50 1 I I 1 I I I 0 10 20 30 40 50 60 70 C.W  %

Figure 2-10 Tensile Strength of Cold Rolled and Aged Modified Alloy 718, Conventional Alloy 718 and Alloy X-750 (Reference 3)

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14 0 Modified Alloy 718 1010°C/lh+CW+704=C/6h (Heat J1) 0 A ConventionalAlloy 718 101 0 °C/1h+CW+718°C/8h-621°C/8h (HeatJ2) t-O 0 Alloy X-750 0

1093 CIih+CW+704°C/20h (Heat RE2) 0 20 w -

10-- - A--._

L 0! I I I I t 0 10 20 30 40 50 60 70 C.W. %

Figure 2-11 Elongation of Cold Rolled and Aged Modified Alloy 718, Conventional Alloy 718 and Alloy X-750 (Reference 3)

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Toshiba Proprietary Information Figure 2-12 Hardness of Modified Alloy 718 Compared to Alloy X-750 SMV-201 1-000034-NP Rev.0

15 2.8 SCC SUSCEPTIBILITY IN HIGH AND LOW TEMPERATURE WATER Resistance to SCC initiation in high temperature water was evaluated by CBB (Creviced Bent Beam) test (refer to Figure 2-15). Specimens (50 mm x 10 mm x 2 mm) were bent along the device with the curvature of 100 mm in radius, and a constant strain of 1% was applied in the outer surface of the specimens. Graphite wool, the material chosen to form the crevice, was attached to the outer surface of specimens. Test specimens were exposed to the high temperature water (550'F (288QC)) for 500 hours0.00579 days <br />0.139 hours <br />8.267196e-4 weeks <br />1.9025e-4 months <br /> in an autoclave installed in a recirculating loop. Table 2-5 shows CBB test results of modified alloy 718 in 288'C pure water (20 ppm 02). Figure 2-13 shows micro-observation results for a cross-section of modified alloy 718 test specimen after the CBB test. Modified alloy 718 shows no cracking in all specimens. SCC susceptibility of modified alloy 718 is extremely low compared to that of alloy X-750 (see Figure 2-14). The figure shows SCC crack depth of modified alloy 718, alloy X-750, and sensitized type 304 stainless steel after CBB test in high temperature water with various chloride content (288°C, 8 ppm 02) (Reference 3). Alloy X-750 is most susceptible to SCC in almost all of the range of chloride content. Next is sensitized type 304 stainless steel. Modified alloy 718 is nearly immune to SCC in the range of less than 50 ppb of chloride content. Figure 2-16 shows chromium profiles perpendicular to the grain boundaries of modified alloy 718 and alloy X-750 (Reference 3). Figure 2-16 also shows the Transmission Electron Microscope (TEM) photos near the grain boundaries of modified alloy 718, and alloy X-750 (Reference 3). No precipitate is visible on the grain boundaries of modified alloy 718. However, large chromium carbides form on the grain boundary of alloy X-750. Modified alloy 718 has no chromium depletion like that observed in alloy X-750. A long-term uni-axis constant load (UCL) test was also conducted for modified alloy 718 and alloy X-750 to evaluate resistance to SCC initiation in high temperature water. The test specimen was loaded by the piston upon which the force is generated by the initial pressure of high temperature water. Applied stress was varied by changing the diameter of the specimens. Graphite wool was used to create a crevice around the gage section of the specimen. Test machines were equipped in high temperature water loop (288°C, 8 ppm 02). Figure 2-17 shows the applied stress of modified alloy 718 and alloy X-750 (Reference 7). Tests of modified alloy 718 for 10,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> were conducted.

Modified alloy 718 showed no failure for 10,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> at applied stress beyond the yield strength (700-800 MPa in 288°C). The margin of SCC initiation for applied stress of modified alloy 718 is higher than that of alloy X-750. Modified alloy 718 has excellent resistance to high temperature SCC.

Section 2.11.2 describes the rising load test and how it evaluated resistance to SCC initiation in low temperature water.

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16 Content Deleted -

Toshiba Proprietary Information Figure 2-13 Micro-Observation for Cross-Section of Test Specimen after CBB Test l-owo 8

U- 5w?

718 CF Concentrolion, ppb Figure 2-14 CBB Test Results for Modified Alloy 718, Alloy X-750, and 304SS (288°C Water - 8 ppm 02) (Reference 3)

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17

[Table 2-5 CBB Test Result Content Deleted -

Toshiba Proprietary Information Graphite Wool Specimen Spacer

--I7""DO:Temperature: 288 C 0 in " Applied Strain: 1%

20ppm

" Test time: 500 h 20 Figure 2-15 CBB (Creviced Bent Beam) Test Device 2.9 GRAIN BOUNDARY ANALYSIS As mentioned in Section 2.8, Figure 2-16 shows chromium profiles perpendicular to the grain boundaries of modified alloy 718 and alloy X-750 (Reference 3). Figure 2-16 also shows the Transmission Electron Microscope (TEM) photos near the grain boundaries of modified alloy 718, and alloy X-750 (Reference 3). No precipitate is visible on the grain boundaries of the modified alloy 718. However, large chromium carbides form on the grain boundary of alloy X-750. Modified alloy 718 has no chromium depletion like that observed in alloy X-750.

To summarize, no chromium depletion near the grain boundaries of modified alloy 718 were observed by TEM analysis.

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18 0 -"

Chromium carbides forms on the grain boundaries of o -conea X-750 41093-C/lb + 704"C/201¶)

U alloy X-750 (1093*C/Ih +7D4T/Zh) (Heat RE2) 0.6- (Heat RE2) to Any precipitate cannot be 08,, ti e IC/I n(1°,°./ih + 704"CAN lf*olEoecCe 718 visible on the grain boundaries of modified 08 tl10",'*

• 04"/6m* "Modiffied Alloy 718 I

alloy 718 5, 06 Mlodifled Alloy 718 (Heat J1) (Heat J1)

.. 500 1000 Ref M. Tsubota. K Hatton, T. Kaneko and T. Okada, G .

D$tonme From Grain Bloundary, nm

-SCC SuscepbzbdityofAlloy718, Proceedings

1996 Workshop on Advanced High-Strength Materials, EPRI NP-6363, PaperIS. May 1989.

Figure 2-16 Chromium Profiles at Grain Boundaries for Modified Alloy 718 and Alloy X-750 (Reference 3) 2.10 LONG-TERM CONSTANT LOAD TEST As discussed in Section 2.8, Figure 2-17 shows the applied stress of modified alloy 718 and alloy X-750 (Reference 7). Long-term UCL (Uni-axis Constant Load) tests of modified alloy 718 for 10,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> were conducted. Modified alloy 718 showed no failure for 10,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> at applied stress beyond the yield strength (700-800 MPa in 288°C). The margin of SCC initiation for applied stress of modified alloy 718 is higher than that of alloy X-750. Modified alloy 718 has excellent resistance to high temperature SCC.

900

~70 sow

~5O J400 Ref. 1) Japanese utllity joint study, "Investigation of Corrosion Resistance of High Strength Nickel

~3o Base Alloy," Final Report, Match 1999.

200 2) M. Tsubota and Y. Kanazawa, "Predicton of the Crack Initiation Time of the Alloys used in 100 High Temperature Water" CORROSION 94.

Paper No.238 (1994).

0 0 2000 4000 6000 )000 10000 12000 Teot Time (hr)

Figure 2-17 UCL Test Result of Modified Alloy 718 and Alloy X-750 (Reference 7)

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19 2.11 REQUIRED TESTS IN BWRVIP-84 AND BWRVIP-138 The following tests for modified alloy 718 were conducted in order to obtain the material property data required in EPRI BWRVIP.

• Rising Load Test (BWRVIP-84)

• SCC Crack Growth Rate Test (BWRVIP-138)

The rising load test is required to evaluate SCC resistance of the material in low temperature water environment.

The SCC crack growth rate test is required to evaluate SCC growth behavior and set up the periodical inspection intervals for Jet-Pump Beam.

2.11.1 RISING LOAD TEST PROCEDURE A rising load test was conducted in accordance with Appendix A of MIL-DTL-24114F(SH), Nickel-Chromium-Iron Age-Hardenable Alloy, Rods, and Forgings (ANSI Approved). The rising load test conducted is shown in Figure 2-18.

- Notch plus pre-cracking specimen C,,^N,^ RAM(0.18 to 0.22 Inch depth) was

,I- M, r---0 ý IN-Pf R , introduced.

,,,, ,,I WAIbFR M

-3 point bending load was applied to R I AIRspecimen with constant AN,* .I displacement rate (0.002 inch per

' minute) in aerated 200" F(93'*C) water (deionized water).

Acceptnce Criteria in BNVRV*IP-8 SLAL WED-Average drop-off time from maximum load to

______--_a/- z maximum load shall be equal to or greater LOAL(FttIHINSILEMALVINh / P-E than 4 minutes.

No specimen shall display a value less zYb than 2 minutes.

Figure 2-18 Rising Load Test Procedure 2.11.2 RISING LOAD TEST RESULT Resistance to SCC initiation in low temperature water was evaluated by a rising load test in accordance with MIL-DTL-24114F(SH) Appendix A (Reference 2). A notch plus pre-cracking (0.18 inch to 0.22 inch depth) was introduced to the specimen. A 3-point bending load was applied to the specimen with a constant displacement rate (0.002 inch per minute) in aerated 200'F (93'C) water (deionized water). The rising load test acceptance criteria for alloy X-750 are defined in BWRVIP-84, SMV-201 1-000034-NP Rev.0

20 which states that average drop-off time from maximum load to 1/2 maximum load shall be equal to or greater than 4 minutes, and no specimen shall display a value less than 2 minutes (Reference 10).

Figure 2-19 and Figure 2-20 show drop-off time from maximum load to 1/2 maximum load of modified alloy 718 and alloy-X-750 after the rising load test. Both modified alloy 718 and alloy X-750 satisfy the criteria for alloy X-750 in BWRVIP-84. However, the time of modified alloy 718 is about 15 times longer than that of alloy X-750. It was confirmed that modified alloy 718 has excellent resistance to low temperature SCC.

All specimens of modified alloy 718 displayed large lateral deformation. All specimens of alloy X-750 showed little lateral deformation. The results of the macro-observation of fracture surface after the rising load test for modified alloy 718 and alloy X-750 are shown in Figure 2-21 and Figure 2-22.

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Toshiba Proprietary Information Figure 2-19 Drop-Off Time for Alloy X-750 and Modified Alloy 718 for All Data Content Deleted -

Toshiba Proprietary Information.

Figure 2-20 Drop-Off Time for Alloy X-750 and Modified Alloy 718 for Average SMV-2011-000034-NP Rev.0

21 Content Deleted -

Toshiba Proprietary Information Figure 2-21 Macro-Observation of Fracture Surface after Rising Load Test for Modified Alloy 718 Content Deleted -

Toshiba Proprietary Information Figure 2-22 Macro-Observation of Fracture Surface after Rising Load Test for Alloy X-750 SMV-2011-000034-NP Rev.0

22 2.11.3 SCC CRACK GROWTH RATE TEST PROCEDURE SCC crack growth rate test using 0.5TCT specimens was conducted under constant load condition.

The crack length was monitored with potential drop method (PDM).

Test Conditions:

• Temperature: 288'C

• Water Chemistry: NWC (ECP _Ž150m VSHE)

• Conductivity: Inlet < 0.1 pS/cm, Outlet < 0.2 pS/cm

• Stress Intensity Factor (K): 30-50 MPa-m Proposed SCC Crack Growth Rate Curves for X-750 in BWRVIP-138 are shown in Figure 2-23.

PeopowdC=A Grow& Rts ft NX-Mforum. a HM aWN 4ýý3 AGEN f Proposed SCC Crack Growth Rate Curves for X-750 in BWRVIP-1 38 E

A (44.0) (55.0)

• lI lX' ,

(7.1X 10-)s

):MP8,m Figure 2-23 Proposed SCC Crack Growth Rate Curves for X-750 in BWRVIP-138 2.11.4 SCC CRACK GROWTH RATE TEST RESULT Resistance to SCC propagation in high temperature water was evaluated by crack growth rate test under a constant load condition. 0.5TCT specimen (B=12.7 mm, W=25.4 mm) was used for the test at 30 to 60 MPa Fm of stress intensity factor (K). The crack growth test was conducted in an autoclave installed in a recirculating loop. The crack lengths were monitored by means of the reversing DC potential drop method (PDM). The dissolved oxygen (DO) concentration was controlled to be more than 15ppm to adjust corrosion potential to be more than 150 mV-SHE simulating NWC condition. Table 2-6 and Figure 2-24 show the relation between SCC growth rate and K for modified alloy 718 and alloy X-750. SCC growth rate data for alloy X-750 is below the proposed curves in BWRVIP-138 (Reference 1). SCC growth rate for modified alloy 718 is much lower (more than 1 order of magnitude lower) than that for alloy X-750.

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23 I Table 2-6 Crack Growth Rate for Materials Content Deleted -

Toshiba Proprietary Information Content Deleted -

Toshiba Proprietary Information Figure 2-24 SCC Growth Rate Data for Modified Alloy 718 and Alloy X-750 2.12 FATIGUE PROPERTY Fatigue property in air was evaluated by fatigue testing under a cyclic load condition. Load-controlled fatigue tests (stress ratio: -1) were conducted in accordance with ASTM E 466 (Reference

5) under the condition of the stress amplitude below the yield strength. Test specimens based on ASTM E 466 Fig. 1 were used in load-controlled fatigue tests. Strain-controlled fatigue tests (strain ratio: -1) were conducted in accordance with ASTM E 606 (Reference 4) under the condition of the stress amplitude beyond the yield strength. Test specimens based on ASTM E 606 Fig. 1 were used in strain-controlled fatigue tests. In the strain-controlled fatigue tests, stress value (a) was calculated from strain value (c) and Young's modulus (E) (a=cE , E (RT)= 203 GPa (29.4x 106 psi), E (302 0C (576°F))= 191GPa (27.7xx1I 6 psi)). Figure 2-25 shows fatigue test results for modified alloy 718 and SMV-2011-000034-NP Rev.0

24 alloy X-750 (Reference 7). Modified alloy 718 has high fatigue strength. Fatigue life of modified alloy 718 is longer than that of alloy X-750 and hence is superior to alloy X-750.

10 4 C,,

E (n

4-I C,,

102 103 104 105 106 107 10 8 Fatigue Life Nf ( Number of cycles ) RT: Room Temperature (1) Strain-controlled fatigue testing (Strain ratio: -1)

(2) Load-controlled fatigue testing (Stress ratio: -1)

Figure 2-25 Fatigue Test Results for Modified Alloy 718 and Alloy X-750 (Reference 7) 2.13 RADIATION RELAXATION RATE Alloy 718 has similar radiation relaxation rates in comparison to alloy X-750. See Figure 2-26 and Figure 2-27 (References 8 and 9).

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25 Inconel X-750 I.0

= 215.6 MPa

"*,.*3000C

' 0.5 b

b IIn-reactor results by Cousey et al.

I I t 0

0 I. 2 dpo Fig. 3. Calculated stress relaxation of Inconel X-750 at 300*C, 3 X10-8 dpa/s with experimental data of the similar condi-tion.

Figure 2-26 Stress Relaxation of X-750 in an Irradiated Environment (Reference 9)

1. Ii, v-

-m-: mmuured, T = 3 16C 0

0.81 vbrzine et al. [10), T =31 CC 06 0.4 I I I I 0 0.2 0.4 0.6 0.8 1.0 cdose [dpa]

Fig. 4. Stress relaxation for Inconel 718. The hollow circle represents bend stress relaxation measured after in-pile irradi-ation at 315°C [10).

Figure 2-27 Stress Relaxation of 718 in an Irradiated Environment (Reference 8)

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26 2.14 SPRING PROPERTY OF JET-PUMP BEAM The spring property of a jet pump beam was tested as shown in Figure 2-28 (Reference 7). The results of the test, which is a comparison of the modified alloy 718 to alloy X-750 jet pump beams, are shown in Figure 2-29 (Reference 7). The test results are summarized below.

• Bending tests for Jet Pump Beams were conducted at applied load of 50 tonx 1 cycle.

• Apparent permanent strain remained in alloy X-750 beam after the bending test.

• No permanent strain remained in modified alloy 718 beam after the bending test.

This testing demonstrates that modified alloy 718 has superior spring property compared to alloy X-750.

JMt-Puuv Beam attached suvi. ppm Figure 2-28 Spring Property of a Jet-Pump Beam (Reference 7) 2 6 Modified Alloy 718 Heat ID: JPB1 [ Alloy X-750 Heat ID: JPB2 (Jet-Pump Beam) (Jet-Pump Beam) 40---

30 4 - -.. - - -

T1',-

5 Permane=t Str0in S' Figure 2-29 Load vs Strain Curves for Modified Alloy 718 and Alloy X-750 (Reference 7)

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27 2.15

SUMMARY

OF MATERIAL PROPERTY TESTS AS RELATED TO JP BEAMS The testing has demonstrated that modified alloy 718 has superior ductility, fatigue and spring properties, as well as greater resistance to SCC initiation and crack growth than alloy X-750 (See Table 2-7). As such, modified alloy 718 can be applied as an alternative material to alloy X-750 for jet pump beams. Note that Toshiba has proposed to include modified alloy 718 in the BWRVIP-84 Appendix.

Table 2-7 Summary of Material Properties of Modified Alloy 718 Mechanical Resistance to SCC Resistance to SCC Fatigue Property Property Initiation (Low Propogation and High Temp.)

Modified Alloy 718 0 Strength Ductility Superior to alloy X-750 0 : Similar to alloy X-750 Modified Alloy 718 is defined in ASME Code Case N-60-6 as grade 718 type 2. The code case is approved as of December Balloting. The Issued Code Case from ASME will be published in Supplement 8 of the 2010 Edition and cannot be expected to be available for several months, minimum, possibly up to six months. Included as Attachment 2 is a clean version of the code case revisions just to include the Modified 718 material. When published, ASME Code Case N-60-6 will look different because other changes will have also been incorporated. The modified alloy 718 is in full compliance with the ASME approved code case requirements specified as grade 718 type 2.

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28 3 REFERENCES

1. Toshiba report PM-2009-0162, Rev. 1, June 2011, Material Properties of Modified Alloy 718 For Use in BWR Internals.

2. Navy Military Specification, MIL-DTL-24114F(SH) Appendix A.

3. M. Tsubota, K. Hattori, T. Kaneko and T. Okada, "SCC Susceptibility of Alloy 718,"

Proceedings : 1986 Workshop on Advanced High-Strength Materials, EPRI NP-6363, Paper 18, May 1989.

4. ASTM E 606 - 04, Standard Practice for Strain Controlled Fatigue Testing, 2005.

5. ASTM E 466 - 07, Standard Practice for Conducting Force Controlled Constant Amplitude Axial Fatigue Tests of Metallic Materials.

6. BWRVIP-138, Revision 1: "BWR Vessel and Internals Project, Updated Jet Pump Beam Inspection and Flaw Evaluation Guidelines," EPRI Technical Report 1016574, December 2008.

7. Y. Katayama, M. Tsubota, Y. Saito, N. Tanaka and S. Tanaka, "SCC Properties of Modified Alloy 718 in BWR Plant," 15 th International Conference on Environmental Degradation of Materials in Nuclear Power Systems - Water Reactors, August 7-11, 2011.

8. Journal of Nuclear Materials, "Proton irradiation creep of Inconel 718 at 300'C," R. Scholz and R.

Matera, 2000.

9. Journal of Nuclear Materials, "Calculation of radiation-induced stress relaxation," J. Nagakawa, 1995.

10. BWRVIP-84-Revision 1: BWR Vessel Internals Project, "Guidelines for Selection and Use of Materials for Repairs to BWR Internal Components," Final Report, EPRI, August 2011.

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Attachment 1 Cross Reference Table - VIP84 RI Requirements for X-750 vs.

Fabrication Methods Utilized for Alloy 718 JP Beam SMV-2011-000034-NP Rev.O

Content Deleted -

Toshiba Prourietarv Information

Attachment 2 Code Case 60-N-6 SMV-2011-000034-NP Rev.O

CASE N-60-6 CASES OF ASME BOILER AND PRESSURE VESSEL CODE Approval Date: December 6, 2011 See Numeric Index for expiration and any reaffirmation dates.

Case N-60-6 (a) All other requirements of Subsection NG of Section III, Division 1, shall be met.

Material for Core Support Structures (b) Strain hardened SA-479 shall be identified Section III, Division 1 with this Case number.

(c) Where welds are applied to strain hardened Inquiry: What materials, in addition to those material, the stress intensity in the sections of listed in Tables 2A, 2B, and 4,Section II, Part the material where the temperatures during D, Subpart 1, may be used for core support welding exceed 8007F shall not exceed values structures constructed to the requirements of for annealed materials.

Subsection NG of Section III, Division 1? (d)Yield strength values are listed in Table B.

(e) Tensile strength values are listed in Table C.

Reply: It is the opinion of the Committee that 69 Chemical composition for Ni-Cr-Fe ASTM B the materials and stress intensity values listed in 637 Types 1 and 2 is listed in Table D.

Table A may be used in the construction of core (g)Heat treatments for Ni-Cr-Fe ASTM B 637 support structures in addition to those listed in Types 1 and 2 and Grade 718 Type 2 are listed Tables 2A, 2B and 4,Section II, Part D, Subpart in Table E.

1. The following additional requirements shall (h) Room temperature mechanical properties for be met. Ni-Cr-Fe ASTM B 637 Types 1 and 2 and Grade 718 Type 2 are listed in Table F.

The Committee's function is to establish rules of safety, relating only to pressure integrity,.governing the construction of boilers, pressure vessels, transport tanks and nuclear components, and inservice inspection for pressure integrty of nuclear components and transport tanks, and to interpret these rules when questions arise regarding their intent. This Code does not address other safety issues relating to the construction of boilers, pressure vessels, transport tanks and nuclear components, and the inservice inspection of nuclear components and transport tanks. The user of the Code should refer to other pertinent codes, standards, laws, regulations or other relevant documents.

1 (N-60-6)

CASE (continued)

N-60-6 TABLE A Min.

Type Min Ult. Stress Intensity, ksi, Nominal S Prod. Spec. or Yield Tens. For Metal Temperature, OF, Not to Exceed Composition No. Form No. Grade Nc tes Str. Str. 100 200 300 400 500 600 650 700 750 800 13Cr 6 Plate SA-240 TP-410 30.0 60.0 20.0 18.4 17.7 17.4 17.2 16.8 16.5 16.2 15.7 15.1 22Cr-13Ni-5Mn ... Plate SA-240 XM-19 7,8 55.0 100.0 33.3 33.2 31.4 30.2 29.7 29.2 29.0 28.8 28.5 28.2 22Cr-13Ni-5Mn ... Bar A 479-74 XM-19 7,8 55.0 100.0 33.3 33.2 31.4 30.2 29.7 29.2 29.0 28.8 28.5 28.2 18Cr-8Ni 8 FFBS SA-193 B8 7 30.0 75.0 20.0 20.0 20.0 18.7 17.4 16.4 16.1 15.9 15.5 15.1 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 7 30.0 75.0 20.0 20.0 20.0 19.2 17.9 17.0 16.6 16.3 16.0 15.8 18Cr-iONi-Ti 8 FFBS SA-193 B8T 7 30.0 75.0 20.0 20.0 20.0 19.2 17.9 17.0 16.6 16.3 16.0 15.8 18Cr-iONi-Cb 8 FFBS SA-193 B8C 7 30.0 75.0 20.0 20.0 20.0 20.0 19.9 19.3 18.9 18.6 18.4 18.3 26Ni-1 5Cr-2Ti ... FFBS SA-453 660 5,7 85.0 130.0 43.3 43.3 43.3 43.3 43.3 43.3 43.3 43.3 43.3 42.6 18Cr-8Ni 8 Smls Tube A 511-71 MT304 6,7 30 75 20.0 20.0 20.0 18.7 17.4 16.4 16.1 15.9 15.5 15.1 18Cr-8Ni 8 Smls Tube A 511-71 MT304L 6,7 25 70 16.6 16.6 16.6 15.7 14.7 13.9 13.7 13.4 13.2 13.0 16Cr-12Ni-2Mo 8 Smls Tube A 511-71 MT316 6,7 30 75 20.0 20.0 20.0 19.2 17.9 17.0 16.6 16.3 16.0 15.8 16Cr-12Ni-2Mo 8 Smls Tube A 511-71 MT316L 6,7 25 70 16.6 16.6 16.6 15.5 14.4 13.5 13.2 12.8 12.6 12.3 18Cr-8Ni 8 Weld Tube A 554-72 MT304 6,7 30 75 20.0 20.0 20.0 18.7 17.4 16.4 16.1 15.9 15.5 15.1 18Cr-8Ni 8 Weld Tube A 554-72 MT304L 6,7 25.0 70.0 16.6 16.6 16.6 15.7 14.7 13.9 13.7 13.4 13.2 13.0 16Cr-12Ni-2Mo 8 Weld Tube A 554-72 MT316 6,7 30 75 20.0 20.0 20.0 19.2 17.9 17.0 16.6 16.3 16.0 15.8 16Cr-12Ni-2Mo 8 Weld Tube A 554-72 MT316L 6,7 25.0 70.0 16.6 16.6 16.6 15.5 14.4 13.5 13.2 12.8 12.6 12.3 Ni-Cr-Fe ... FFBS SB-637 688 9 40 100 26.7 26.1 25.5 25.1 24.6 24.3 24.1 24.0 23.9 23.8 Ni-Cr-Fe *. FFBS SB-637 688 5,10 90 140 46.7 46.7 46.7 46.7 46.7 46.7 46.7 46.7 46.7 46.5 Ni-Cr-Fe ... FFBS SB-637 688 5,11 115 170 56.7 56.7 56.7 56.7 56.7 56.7 56.7 56.7 56.7 56.5 Ni-Cr-Fe ... FFBS SB-637 688 5,12 100 160 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.3 53.1 Ni-Cr-Fe 43 Plate SB-168 ... 15 35 80 23.3 23.2 23.3 23.3 23.3 23.3 23.3 23.3 23.3 23.3 Ni-Cr-Fe .. FFBS B 637 TP-1 5 100 160 53.3 53.3 53.3 53.3 53.3 53.2 52.7 52.1 51.5 ...

Ni-Cr-Fe ... FFBS B 637 TP-2 5 85 150 50.0 50.0 50.0 50.0 50.0 50.0 50.0 50.0 50.0 ...

Ni-Cr-Fe SB-637 718 Type 2 100 160 53.3 53.3 53.3 53.3 52.4 51.2 50.6 50 49.4 16Cr-12Ni-2Mo 8 FFBS SA-479 316 1,2,7 ,13 60 85 28.3 28.3 26.8 25.9 25.7 25.7 25.7 25.7 25.7 25.4 16Cr-12Ni-2Mo 8 FFBS SA-479 316 1,2,7 ,14 65 85 28.3 28.3 26.8 25.9 25.7 25.7 25.7 25.7 25.7 25.4 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,7 50 90 30.0 30.0 28.3 27.4 26.8 26.4 26.1 25.7 25.2 24.6 16Cr-1 2Ni-2Mo 8 FFBS SA-193 B8M 1,2,7 65 90 31.6 31.6 29.9 29.0 28.7 28.7 28.7 28.7 28.7 28.4 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,3 ,5,7 80 100 33.3 33.3 31.5 30.5 30.2 30.2 30.2 30.2 30.2 29.9 16Cr-12Ni-2Mo 8 FFBS SA-193 B8M 1,2,4 ,5,7 95 110 36.6 36.6 34.6 33.5 33.3 33.3 33.3 33.3 33.3 32.8 See following page for notes.

2 (N-60-6)

CASE (continued)

N-60-6

[Notes to Table A]

NOTES:

(1) Strain hardened. (The tensile properties for these items shall meet the minimum specified. These materials shall conform to all other requirements of the referenced specification. Surface hardness as shown in SA-479 is not required.)

(2) Yield strength values are listed in Table B.

(3) Maximum tensile strength-140,000 psi.

(4) Maximum tensile strength-150,000 psi.

(5) The designer shall consider the effects of temperature and environment on the material properties of precipitation hardening alloys and cold worked austenitic stainless steels.

(6) Supplementary requirement S-2 for tensile testing of the specification is mandatory.

(7) At temperatures above 100°F, the design stress intensity values may exceed 662,3% and may also reach 90% of the yield strength (0.2% offset) at temperature. This may result in a permanent strain of as much as 0.1%. When this amount of deformation is not acceptable, the designer should reduce the design stress intensity to obtain an acceptabledeformation.Section III, Division 1, Table 1-2.4 lists multiplying factors which, when applied to the yield strength values shown on Table 1-2.2, will give a design stress intensity that will result in lower levels of permanent strain.

(8) The Sy values for Type XM-1 9 stainless steels vary with the annealing temperature (see Table B).

(9) Solution heat treated.

(10) Type 1.

(11) Type 2.

(12) Type 3.

(13) Over 2 in.

(14) Up to and including 2 in.

(15) Hot finished.

3 (N-60-6)

CASE (continued)

N-60-6 TABLE B Yield Strength Values Sy Spec. Yield Strength (Ksi) for Metal Temperature 'F, Not to Exceed Nominal Prod. Type or Composition Form Spec. No. Grade Notes Min. Yield 100 200 300 400 500 600 650 700 750 800 18Cr-8Ni Smis Tube A 511-71 MT304 ... 30.0 30.0 25.0 22.5 20.7 19.4 18.2 17.9 17.7 17.3 16.8 18Cr-8Ni Smis Tube A 511-71 MT304L ... 25.0 25.0 21.3 19.1 17.5 16.3 15.5 15.2 14.9 14.7 14.4 16Cr-12Ni-2Mo Smis Tube A 511-71 MT316 ... 30.0 30.0 25.8 23.3 21.4 19.9 18.8 18.5 18.1 17.8 17.6 16Cr-12Ni-2Mo SmIs Tube A 511-71 MT316L ... 25.0 25.0 21.1 18.9 17.2 15.4 15.0 14.6 14.3 14.0 13.7 18Cr-SNi Wid Tube A554-72 MT304 ... 30.0 30.0 25.0 22.5 20.7 19.4 18.2 17.9 17.7 17.3 16.8 18Cr-8Ni WId Tube A554-72 MT304L ... 25.0 25.0 21.3 19.1 17.5 16.3 15.5 15.2 14.9 14.7 14.4 16Cr-12Ni-2Mo Wld Tube A 554-72 MT316 ... 30.0 30.0 25.8 23.3 21.4 19.9 18.8 18.5 18.1 17.8 17.6 16Cr-12Ni-2Mo WId Tube A 554-72 MT316L ... 25.0 25.0 21.2 18.9 17.2 15.9 15.0 14.6 14.3 14.0 13.7 Ni-Cr-Fe FFBS SB-637 688 3 40.0 40.0 39.1 38.3 37.6 36.9 36.4 36.2 36.0 35.9 35.7 Ni-Cr-Fe FFBS SB-637 688 4 90.0 90.0 87.7 86.4 85.3 84.5 84.1 83.9 83.8 83.7 83.6 Ni-Cr-Fe FFBS SB-637 688 5 115.0 115.0 112.0 110.2 109.0 108.0 107.5 107.2 107.0 106.9 106.8 Ni-Cr-Fe FFBS SB-637 688 6 100.0 100.0 99.0 95.2 94.0 93.1 92.5 92.2 92.0 91.9 91.8 Ni-Cr-Fe FFBS B 637 TP-1 ... 100.0 100.0 97.1 95.2 93.4 92.0 90.0 90.4 90.1 89.9 ...

Ni-Cr-Fe FFBS B 637 TP-2 ... 85.0 85.0 82.4 81.2 80.4 79.9 79.8 79.8 79.8 79.8 ...

Ni-Cr-Fe SB-637 718 Type 2 100.0 100.0 95.5 93.0 91.8 91.1 90.3 89.7 88.9 88.2 ...

16Cr-12Ni-2Mo FFBS SA-479 316 7 60.0 60.0 55.1 52.1 49.8 48.3 47.5 47.0 46.3 45.4 44.5 16Cr-12Ni-2Mo FFBS SA-479 316 8 65.0 65.0 59.8 56.5 54.0 52.3 51.4 50.9 50.1 49.1 48.1 Ni-Cr-Fe Plate SB-168 9 35.0 35.0 32.7 31.0 29.8 28.8 27.9 27.4 27.0 26.5 26.1 16Cr-12Ni-2Mo FFBS SA-193 B8M ... 50.0 50.0 46.0 43.5 41.5 40.3 39.6 39.2 38.6 37.8 37.0 16Cr-12Ni-2Mo FFBS SA-193 B8M ... 65.0 65.0 59.8 56.5 54.0 52.3 51.4 50.9 50.1 49.1 48.1 16Cr-12Ni-2Mo FFBS SA-193 B8M ... 80.0 80.0 73.5 69.6 56.5 64.5 53.3 62.6 61.8 60.5 59.0 16Cr-12Ni-2Mo FFBS SA-193 B8M ... 95.0 95.0 87.5 82.6 78.9 76.5 75.1 74.4 73.3 71.9 70.5 22Cr-13Ni-5Mn Plate SA-240 XM-19 1 55.0 55.0 47.0 43.4 40.8 38.8 37.3 36.8 36.3 35.8 35.3 22Cr-13Ni-5Mn Bar A 479-74 XM-19 1 55.0 55.0 47.0 43.4 40.8 38.8 37.3 36.8 36.3 35.8 35.3 22Cr-13Ni-5Mn Plate SA-240 XM-19 2 55.0 55.0 44.6 39.3 35.7 33.3 32.0 31.5 31.4 31.2 31.1 22Cr-13Ni-5Mn Bar A 479-74 XM-19 2 55.0 55.0 44.6 39.3 35.7 33.3 32.0 31.5 31.4 31.2 31.1 NOTES:

(1) For material annealed at 1925-19757F.

(2) For material annealed at 2025-2075°F.

( 3 ) Solution heat treated.

(4) Type 1.

(5) Type 2.

(6) Type 3.

(7) Over 2 in.

(8) Up to and including 2 in.

(9) Hot finished.

4 (N-60-6)

CASE (continued)

N-60-6 TABLE C MATERIALS PROPERTIES, SUBSECTION NG TENSILE STRENGTHS, Su Tensile Strength Values, Su (ksi), for Austenitic Steel and High Nickel Alloys for Class I Components Spec. Temperature, °F CNominal Prod. Spec. Type or Spec. Min.

Composition Form No. Grade T.S. 100 200 300 400 500 600 650 700 750 800 18Cr-8Ni FFBS SA-193 B8 75.0 75.0 70.9 66.0 64.3 63.5 63.5 63.5 63.5 63.2 62.6 16Cr-12Ni-2Mo FFBS SA-193 B8M 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.5 71.0 18Cr-10Ni-Ti FFBS SA-193 B8T 75.0 75.0 73.4 67.3 68.5 68.5 68.5 68.5 68.5 68.5 68.5 18Cr-10Ni-Cb FFBS SA-193 B8C 75.0 75.0 71.8 66.0 61.9 60.2 59.4 58.9 58.5 58.5 58.5 26Ni-15Cr-2Ti FFBS SA-453 660 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 18Cr-8Ni Smis. Tube A 511 MT304 75.0 75.0 70.9 66.0 64.3 63.5 63.5 63.5 63.5 63.2 62.6 18Cr-8Ni Smis. Tube A 511 MT304L 70.0 70.0 66.2 60.8 58.5 57.7 57.0 56.6 56.2 55.8 55.4 16Cr-12Ni-2Mo Smls. Tube A 511 MT316 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.5 71.0 16Cr-12Ni-2Mo Smis. Tube A 511 MT316L 70.0 70.0 67.7 63.9 62.4 61.6 61.6 61.6 61.6 61.2 60.8 18Cr-8Ni Wid. Tube A 554 MT304 75.0 75.0 70.9 66.0 64.3 63.5 63.5 63.5 63.5 63.2 62.6 16Cr-12Ni-2Mo Wid. Tube A 554 MT316 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.5 71.0 Ni-Cr-Fe FFBS SB-637 Soln. Treated 688 100.0 100.0 100.0 100.0 100.0 100.0 99.4 98.8 98.5 98.2 98.0 Ni-Cr-Fe FFBS SB-637 Type 1 688 140.0 140.0 140.0 140.0 140.0 140.0 140.0 140.0 140.0 140.0 139.8 Ni-Cr-Fe FFBS SB-637 Type 2 688 170.0 170.0 170.0 170.0 170.0 170.0 170.0 170.0 170.0 170.0 169.8 Ni-Cr-Fe FFBS SB-637 Type 3 688 160.0 160.0 160.0 160.0 160.0 160.0 160.0 160.0 160.0 160.0 159.2 Ni-Cr-Fe FFBS B 637 Type 1 160.0 160.0 156.4 152.7 150.2 147.8 145.2 143.8 142.2 140.4 Ni-Cr-Fe FFBS B 637 Type 2 150.0 150.0 147.2 145.5 144.0 142.5 140.9 140.0 139.1 138.7 Ni-Cr-Fe SB-637 718 Type 2 160.0 160.0 160.0 160.0 160 157.2 153.7 151.8 149,9 148.1 16Cr-12Ni-2Mo FFBS SA-479 316 85.0 85.0 85.0 80.3 77.6 77.1 77.1 77.1 77.1 77.1 76.3 16Cr-12Ni-2Mo FFBS SA-193 B8M 90.0 90.0 90.0 85.1 82.4 81.6 81.6 81.6 81.6 81.6 80.9 16Cr-12Ni-2Mo FFBS SA-193 B8M 100.0 100.0 100.0 94.6 91.5 90.8 90.8 90.8 90.8 90.8 89.6 16Cr-12Ni-2Mo FFBS SA-193 B8M 110.0 110.0 110.0 104.0 100.7 99.9 99.9 99.9 99.9 99.9 98.6 13Cr Plate SA-240 410 60.0 60.0 60.0 58.9 57.7 56.9 55.4 54.5 53.0 51.3 49.1 16Cr-12Ni-2Mo Wld. Tube A 554 MT316L 70.0 70.0 67.7 63.9 62.4 61.6 61.6 61.6 61.6 61.2 60.3 18Cr-8Ni Wld. Tube A 554 MT304L 70.0 70.0 66.2 60.8 58.5 57.7 57.0 56.6 56.2 55.8 55.0 15Cr-26Ni-2Ti FFBS SA-638 660 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 130.0 18Cr-lONi-Cb FFBS SA-182 F347 75.0 75.0 71.8 66.0 61.7 60.2 59.4 58.9 58.5 58.5 58.5 18Cr-8Ni FFBS SA-479 304 75.0 75.0 71.0 66.0 64.3 63.5 63.5 63.5 63.5 63.1 62.6 16Cr-12Ni-2Mo FFBS SA-479 316 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.4 70.9 18Cr-10Ni-Cb FFBS SA-479 347 75.0 75.0 71.8 66.0 61.9 60.2 59.4 58.9 58.5 58.5 58.5 18Cr-8Ni FFBS SA-479 304L 70.0 70.0 66.2 60.8 58.5 57.7 57.0 56.6 56.2 55.8 55.4 16Cr-12Ni-2Mo FFBS SA-479 316L 70.0 70.0 67.9 63.9 62.4 61.6 61.6 61.6 61.6 61.2 60.8 18Cr-8Ni Nuts SA-194 8 75.0 75.0 71.0 66.0 64.3 63.5 63.5 63.5 63.5 63.1 62.6 18Cr-lONi-Cb Nuts SA-194 8C 75.0 75.0 71.8 66.0 61.9 60.2 59.4 58.9 58.5 58.5 58.5 16Cr-12Ni-2Mo Nuts SA-194 8M 75.0 75.0 75.0 73.4 71.8 71.8 71.8 71.8 71.8 71.4 70.9 22Cr-13Ni-5Mn Plate SA-240 XM-19 100.0 100.0 99.5 94.3 90.7 89.1 87.8 87.1 86.5 85.7 84.8 22Cr-13Ni-5Mn Bar A 479-74 XM-19 100.0 100.0 99.5 94.3 90.7 89.1 87.8 87.1 86.5 85.7 84.8 5 (N-60-6)

CASE (continued)

N-60-6 CASES OF ASME BOILER AND PRESSURE VESSEL CODE TABLE D ASTM B 637 TYPES 1 AND 2 CHEMICAL REQUIREMENTS Element Percent Carbon 0.020 - 0.060 Manganese 1.00 max Silicon 0.50 max Phosphorus 0.008 max Sulfur 0.003 max Chromium 14.50 - 17.00 Cobalt 0.050 max 0.050 max Columbium + Tantalum 0.70 - 1.20 Titanium 2.25 - 2.75 Alumunium 0.40- 1.00 Boron 0.007 max Iron 5.00 - 9.00 Copper 0.50 max Zirconium 0.050 max Vanadium 0.10 max Nickel 70.00 min TABLE E ASTM B 637 HEAT TREATMENT Solution Annealing Precipitation Hardening Type 1 1975°F +/- 25 0 F, hold 1 1320°F +/- 25°F, hold 20 h, to 2 h, cool by water or oil +2-0 h, air cool quenching Type 2 1975°F +/- 25 0F, hold 1 to 2 h, cool 1400°F +/- 25°F, hold 100 h, by water or oil quenching +4-0 h, air cool Grade 718 Type 2 18500 to 19220F, hold 1 to 2 h, 13000F +/-15 0 F, hold 6 h cool by water or oil quenching +lh -0 min., air cool TABLE F ASTM.B 637 MECHANICAL PROPERTIES (Minimum Room Ternp ature)

Property Type 1 Type 2 Grade 718 Type 2 Yield strength, psi 100,000 85,000 100,000 Tensile strength, psi 160,000 150,000 160,000 Elongation in 2 in. % 20 20 20 Reduction of area, % 20 20 20 Hardness 267-363 HB 267-363 HB 27-40 RC 27-40 RC 6 (N-60-6)

ENCLOSURE 5 AFFIDAVIT FROM TOSHIBA CORPORATION JUSTIFYING WITHHOLDING PROPRIETARY INFORMATION Nine Mile Point Nuclear Station, LLC December 30, 2011

Affidavit for Withholding Confidential and Proprietary Information from Public Disclosure under 10 CFR § 2.390 UNITED STATES OF AMERICA NUCLEAR REGULATORY COMMISSION In the Matter of Constellation Energy LLC Nine Mile Point Unit 2 AFFIDAVIT I, Tadahiko Torimaru, being duly sworn, hereby depose and state that I am Group Manager, Material Engineering Group, System Design & Engineering Department, Nuclear Energy Systems & Services Division, Power Systems Company, Toshiba Corporation; that I am duly authorized by Toshiba Corporation to sign and file with the Nuclear Regulatory Commission the following application for withholding Toshiba Corporation's confidential and proprietary information from public disclosure; that I am familiar with the content thereof; and that the matters set forth therein are true and correct to the best of my knowledge and belief.

In accordance with 10 CFR § 2.390(b )(ii), I hereby state, depose, and apply as follows on behalf of Toshiba Corporation:

(A) Toshiba Corporation seeks to withhold from public disclosure the documents listed in Attachment 1 of this affidavit, and all information identified as "Proprietary Class 2" therein (collectively, "Confidential Information").

(B) The Confidential Information is owned by Toshiba Corporation. In my position as Group Manager, Material Engineering Group, System Design & Engineering Department, Nuclear Energy Systems &

Services Division, Power System Company, Toshiba Corporation, I have been specifically delegated the function of reviewing the Confidential Information and have been authorized to apply for its withholding on behalf of Toshiba Corporation.

(C) This document contains information regarding Modified alloy 718 material which is used for the fabrication of jet pump beams for the inlet mixer replacement project being performed at Nine Mile Point Unit 2. This document constituting and containing Confidential Information is entirely confidential and proprietary to Toshiba Corporation, as indicated by the phrase "Proprietary Class 2" at the top of their cover pages.

(D) Consistent with the provisions of 10 CFR § 2.390(a)(4), the basis for proposing that the Confidential Information be withheld is that it constitutes Toshiba Corporation's trade secrets and confidential and proprietary commercial information.

(E) Public disclosure of the Confidential Information is likely to cause substantial harm to Toshiba Corporation's competitive position by (1) disclosing confidential and proprietary commercial information about the design, manufacture and operation systems for nuclear power reactors to other parties whose commercial interests may be adverse to those of Toshiba Corporation, and (2) giving such parties access to and use of such information at little or no cost, in contrast to the significant costs incurred by Toshiba Corporation to develop such information.

I -,t Toshiba Corporation has a rational basis for determining the types of information customarily held in confidence by it, and utilizes a system to determine when and whether to hold certain types of information in confidence.

The basis for claiming the information so designated as proprietary is as follows:

(a) The information reveals the distinguishing aspects of a process (or component, structure, tool, method, etc.) where prevention of its use by any of Toshiba Corporation's competitors without license from Toshiba Corporation constitutes a competitive economic advantage over other companies.

(b) It consists of supporting data, including test data, relative to a process (or component, structure, tool, method, etc.), the application of which data secures a competitive economic advantage, e.g., by optimization or improved marketability.

(c) Its use by a competitor would reduce his expenditure of resources or improve his competitive position in the design, manufacture, shipment, installation, assurance of quality, or licensing a similar product.

(d) It reveals cost or price information, production capacities, budget levels, or commercial strategies of Toshiba Corporation, its customers or suppliers.

(e) It reveals aspects of past, present, or future Toshiba Corporation or customer funded development plans and programs of potential commercial value to Toshiba Corporation.

(f) It contains patentable ideas, for which patent protection may be desirable.

There are sound policy reasons behind the Toshiba Corporation system which include the following:

(a) The use of such information by Toshiba Corporation gives Toshiba Corporation a competitive advantage over its competitors. It is, therefore, withheld from disclosure to protect the Toshiba Corporation competitive position.

(b) It is information that is marketable in many ways. The extent to which such information is available to competitors diminishes the Toshiba Corporation ability to sell products and services involving the use of the information.

(c) Use by our competitor would put Toshiba Corporation at a competitive disadvantage by reducing his expenditure of resources at our expense.

(d) Each component of proprietary information pertinent to a particular competitive advantage is potentially as valuable as the total competitive advantage. If competitors acquire components of proprietary information, anyone component may be the key to the entire puzzle, thereby depriving Toshiba Corporation of a competitive advantage.

(e) Unrestricted disclosure would jeopardize the position of prominence of Toshiba Corporation in the world market, and thereby give a market advantage to the competition of those countries.

(f) The Toshiba Corporation capacity to invest corporate assets in research and development depends upon the success in obtaining and maintaining a competitive advantage.

Further, on behalf of Toshiba Corporation, I affirm that:

(a) The Confidential Information is confidential and proprietary information of Toshiba Corporation.

(b) The Confidential Information is information of a type customarily held in confidence by Toshiba Corporation, and there is a rational basis for doing so given the sensitive and valuable nature of the Confidential Information as discussed above in paragraphs (D) and (E).

(c) The Confidential Information is being transmitted to the NRC in confidence.

(d) The Confidential Information is not available in public sources.

(e) Public disclosure of the Confidential Document is likely to cause substantial harm to the competitive position of Toshiba Corporation, taking into account the value of the Confidential Information to Toshiba Corporation, the amount of money and effort expended by Toshiba Corporation in developing the Confidential Information, and the ease or difficulty with which the Confidential Information could be properly acquired or duplicated by others.

Tadahiko Torimaru Group Manager Material Engineering Group Systems Design & Engineering Department Nuclear Energy Systems & Services Division POWER SYSTEMS COMPANY TOSHIBA CORPORATION

Attachment 1 to the Toshiba Affidavit to the NRC (Proprietary Information)

DOCUMENTS ENCLOSED (TO BE WITHELD FROM: PUBLIC DISCLOSURE PER 2.390)

Item Document Description Document Number Revision

1. Toshiba Engineering Report SMV-2011-000034-P 0 Jet Pump Beam Fabrication -

Comparison of Modified Alloy 718 and Alloy X-750 Materials _