ML20148C270

Responds to NRC 800225 Request for Info Re Turbine Disc Integrity in Operating Westinghouse Nuclear Low Pressure Turbines.Application for Withholding & Nonproprietary Version Encl.Proprietary Version Withheld (Ref 10CFR2.790)

ML20148C270
Person / Time
Site:	San Onofre
Issue date:	03/18/1980
From:	Baskin K SOUTHERN CALIFORNIA EDISON CO.
To:	Eisenhut D Office of Nuclear Reactor Regulation
Shared Package
ML19341D841	List: ML20148C270
References
TASK-03-04.B, TASK-RR NUDOCS 8003200642
Download: ML20148C270 (53)

Text

{{#Wiki_filter:. ( Southern California Edison Company [fLC P 0; S O X 6 00 2 2 44 W ALNUT GROVE AVENU E ROSEMEAD C ALIFORNI A 3 f 7 70 K. P. S ASKIN tatt*Most W AN AGER. NWCLE A R ENGtNtt 4lNQ 1343) 5734481 March 16, 19oo .No uceNo.No Director of Nuclear Reactor Regulation Attention: D. G. Eisenhut, Acting Director Division of Operating Reactors U.S. Nuclear Regulatory Commission Wasnington, D.C. 20555 Gentlemen: dubject : Docket No. 50-2C6 Turbine Disc Integrity San Onofre Nuclear Generating Station Unit 1 Enclosed are: 1. One (1) copy - Application for withholding. 2. One (1) copy - Affidavit Ah-00-4. 3 One (1) copy of the letter from J. M. Schmerling, Westinghouse Electric Corporation to Darrell G. Eisenhut, Nuclear Regulatory Commission, March 14, 19o0. 4. One (1) copy - Appendix A (Proprietary) - Responses to Site Specific Guestions. 5 One (1) copy - Appendix B (Non-proprietary) - Responses to Site Specific questions. I The purpose of this letter is to respcod to your request for information of Feoruary 25,19do, relative to turoine disc integrity in operating heatinghouse i nuclear low pressure turoines. Per your request in the subject letter, responses to the generic questions have been cocedinated through a task force wnese representation includes all owners of Westinghouse nuclear low pressure turbines and is chaired by Mr. Wayne Stiede of Ccamonwealta Edison. The concensus responses to tne generic questions have been submittec to you by ) westingneuse at the request of the task force (Enclosure 3). Since we adopt U tne consensus respon'ses as our own, we incorporate those responso by reference. S nptf' gee pan' # pSA, 6 Lpoit i /# f, k @l glo t W f^ 6f d t %O0 3200 G 12 %g g_ t

4 i Darrell G. Sisenhut March 16,1980 The site specific responses contain proprietary information of the Westinghouse Electric Corporation ( Appendix A (Proprietary)). In conformance with the requirements of 10CFR Section 2.790, as amended, of the Commission's regulations, we are enclosing with the submittal an application for withholding fr% puolic disclosure (Enclosure 1) and an affidavit (Enclosure 2). The affidavit sets forth the basis on which the information may be withheld from public disclosure by the Commission. Correspondence with respect to the affidavit or application for withholding snould reference AW-80-4 and should be addressed to Mr. R. Williamson, Manager, Customer Order Engineering, Westingneuse Electric Corporation, Steam Turbine Divisions Lester Branen Box 9175, Philadelphia, Pennsylvania,19113 As discussed in Enclosures 3 ana 4: 1) The largest postulated ratio of crack size to critical crack size is conservatively calculated to be much less than 1.0 (see Enclosure 4, Taele 1, Section G) for all discs at the turbine design overspeed, 2) The results of previous turbine inspections has not revealed stress corrosion cracking problems with San Onofre Unit 1 turbine components, and 3) Previous review of the overall probability of turbine missiles damaging the San Oncfre Unit 1 plant and leading to consequences in excess of the 10CFR Part 100 guidelines indicated that such probability is acceptabily low. Therefore, it is concluded that continued operation of the San Onofre Unit 1 low pressure turbines until the Spring,1960 refueling cutage does not represent an undue risk to public safety. If you have any questions concerning this matter, please let me know. Subscribed on this /f day of h /, 1960. By K. P. Baskin Subscribed and sworn to before me this /9 day of bv /, 1960, r_______________ _g_ S_ __AGNES CRABTREE /' l [ et e meuc.c eremaa / i _ ytgt,f ,/, MCPAL ORG M $ wy Notas/y Public in and for the County of L ::::: 3 Los# Angeles, State of California Encl:sures

D0CKET NO. M*[dh DATE: dd 8d NOTE TO NRC AN'D/0R LOCAL PUBLIC DOCUMENT RCOMS The following ites submitted with letter dated [8 8d fres 674 Mi./ 4 [ /Sg4 is being withheld from public disclosure in accordance with 3ection 2.730. PROPRIETARY INFOR'tATION 0 M6 A ldM ,&S /O, ,j,, N 4 I he2AD).l +1/r-sko Distributi:n Service's Branch

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e e AW-80-4 March 14, 1980 Darrell G. Eisenhut Division of Operating Reactors Of fice of Nuclear Reactor Regulation US Nuclear Regulatory Commission Washington DC 20555 APPLICATION FOR WITHHOLDING PROPRIETARY INFORMATION FROM PUBLIC DISCLOSURE

Subject:

San Onofre Fuclear Generating Station Unit 1 Docket #50-206 Information in Response to NRC Request for Information of February 25, 1980, Relative to Low Pressure Turbine Disc Integrity.

Reference:

Appendix A letter from Robert Dietch to Eisenhut, dated 3/18/80

Dear Mr. Eisenhut:

This application for withholding is submitted by Westinghouse Electric Corporation ("Westinghouse") pursuant to the provisions of paragraph (b)(1) of Section 2.790 of the Commission's regulations. Withholding from public disclosure is requested with respect to the subject information which is further identified in the affidavit accompanying this application. The undersigned has reviewed the information sought to be withheld and is authorized to apply for its withholding on behalf of Westinghouse, STG-TOD. The affidavit accompanying this application sets forth the basis on which the information may be withheld from public disclosure by the Commission and addresses with specificity the considerations listed in paragraph (b)(4) of Section 2.790 of the Commission's regulations. Accordingly, it is respectfully requested that the subject information which is proprietary to Westinghouse and which is further identified in the affi-davit be withheld from public disclosure in accordance with 10CFR Section 2.790 of the Commission's regulations. Correspondence with respect to this application for withholding or the accom-panying af fidavit should be addressed to the undersigned. Very truly yours, l$ ?fY ~ R. Williamson, Manager Customer Order Engineering j Westinghouse Electric Corporation I l )

W h f I 4 ENCLOSURE 2 i 1 1 1 l 1 I i 1 i I e

' s Refe AW-80-4 AFFIDAVIT COMMONWEALTH OF PENNSYLVANIA COUNTY OF DELAWARE: Before me, the undersigned authority, personally appeared Robert Williamson, who, being by me duly sworn according to law, deposes and asys that he is authorized to execute this Affidavit on behalf of Westinghouse Electric Corporation ("Westinghouse") and that the averments of fact set forth in this Affidavit are true and correct to the best of his knowledge, information, and belief: E ?> U Al Robert Williamsen, Manager Customer Order Engineering f,4cm to.aN s:iscib:d f.cre me lass..)..h.... day odf/.}i.i.119.5 1. e - --W.sw(L. ' 35w% p ) HENRY E. SQUILLACE m sac, us. rat. om.u. ca. .Ah CunNsWon bWes Cct.18, IMO l

e, (1) I am Manager, Customer Order Engineering in the Steam Turbine Generator Technical Operations Division of Westinghouse Electric Corporation and as such, I have been specifically delegated the function of reviewing the proprietary information sought to be witcheld from public disclosure in connection with nuclear power plant licensing, and am authorized to apply for its withholding on behalf of the Westinghouse Power Generation Divisions. (2) I am making this Affidavit in conformance with the provisions of 10 CFR Section 2 790 of the Commission's regulations and in conjunction with the Westinghouse application for withholding accompanying this Affidavit. (3) I have personal knowledge of the criteria and procedures utilized by Westinghouse Power Generation Divisions in designating informa-tien as a trade secret, privileged or as confidential commercial or financial information. (4) Pursuant to the provisiens of paragraph (b)(4) of Section 2.790 of the Commission's regulations, the following is furnished for con-sideration by the Commission in determining whether the information sought to be withheld from public disclosure should be withheld. (1) The information sought to be withheld from public disclosure is owned and has been held in confidence by Westinghouse. t (ii) The information is of a type customarily held in confidence by Westinghouse and not customarily disclosed to the pub-lie. Westinghouse has a rational basis for determining the types of information customarily held in confidence by it and, in that connection, utilizes a system to determine when and whether to hold certain types of information in confi-dance. The application of that system and the substance of that system constitutes Westinghouse policy and provides the rational basis required. l 1

-0 I i Under that system, information is held in confidence if it falls in one or more of several types, the release of which right result in the loss of an existing or potential com-u petitive advantage, 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 Westinghouse's ccmpetitors without license from Westinghouse consti-tutes 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 i of quality, or licensing a similar product. l (d) It reveals cost or price information, production capac-ities, budget levels, or commercial strategies of West-inshouse, its customers or suppliers. (e) It reveals aspects of past, present, or future Westing-house or customer funded development plans and programs of potential commercial value to Westinghouse. (f) It contains patentable ideas, for which patent protec-tien may be desirable. (g) It is not the property of Westinghouse, but must be j treated as proprietary by Westinghouse according to agreements with the owner.

i (h) Public disclosure of this information would allow un-fair and untruthful judgments on the performance and reliability of Westinghouse equipment components and improper comparison with similar components made by competitors. There are sound policy reasons behind the Westinghouse system which include the following: (a) The use of such information by Westinghouse gives West-inghouse a competitive advantage over its competitors. It is, therefore, withheld from disclosure to protect the Westinghouse competitive position. (b) It is information which is marketable in many ways. The extent to which such information is available to competitors diminishes the Westinghouse ability to sell products and services involving the use of the information. (c) Use by our competitor would put Westinghouse at a ecm-petitive 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 ecm-petitors acquire components of proprietary information, any one component may be the key to the entire pu::le, thereby depriving Westinghouse of a competitive advantage. (e) Unrestricted disclosure would jeopardi:e the position of pecminence of Westinghouse in the world market, and thereby give a market advantage to the competition in those countries.

i ( f) The Westinghouse capacity to invest corporate assets in research and development depends upon the success in obtaining and maintaining a competitive advantage. ('iii) The information is being transmitted to the Commission in confidence and, under the provisions of 10 CFR Sec-tion 2 790, it is to be received in confidence by the Commission. (iv) The information is not available in public sources to the best of our knowledge and belief. (v) The proprietary informatien sought to be withheld in this submittal is that which is appropriately marked in Appen-dix A to letter from M. P. Baskin Eisenhut, dated March 18, 1980 concerning infor-mation in response to NRC request for information of February 25, 1980, relative to low pressure turbine disc integrity. The information enables Westinghouse to: (a) Develop test inputs and procedures to satisfactorily verify the design of Westinghouse supplied equipment. l l (b) Assist its custcmers to obtain licenses. Further, the information has substantial commercial value as follows. (a) Westinghouse can sell the use of this information to customers. (b) Westinghouse uses the information to verify the design of equipment which is sold to customers.

4 (c) Westinghouse can sell services based upon the exper-ionce gained and the test equipment and methods developed. Public disclosure of this information is likely to cause substantial harm to the competitive position of Westinghouse because it would enhance the ability of competitors to design, manufacture, verify, and sell electrical equipment for commercial turbine-generators without commensurate expenses. Also, public disclosure of the information would enable others having the same or similar equipment to use the information to meet NRC requirements for licensing documentation without purchasing the right to use the information. The development of the equipment described in part by the information is the result of many years of development by Westinghouse and the expenditure of a considerable sum of money. This could only La duplicated by a competitor if he were to invest similar sums of money and provided he had the appro-priate talent available and could somehow obtain the requi-site experience. Further the deponent sayeth not. i t y

'~ 'W w 8 { l l ENCLOSURE 3 i i l i i l l

p_s f: y ) c f </ Westinghouse Power Generation Electric Corporation Group ":r n-" e 7

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, March 14,1980 Darrell G. Eisenhut, Acting Director j Division of Operating Reactors U.S. Nuclear Regulatory Commission Washington, D.C. 20555

Dear Mr. Eisenhut,

Your letters of February 25,1980, to licensees with operating Westinghouse steam turbines requested certain site specific and generic information relative to turbine disc integrity. You urged in your letter that the licensees address the generic questions and coordinate the responses through an owners' group. Licensees with nuclear power plants and Westinghouse steam turbines have formed a Turbine Dise Integrity Task Force, with Mr. Wayne Stiede'of Commonwealth i Edison Company selected as Chairman. Westinghouse has been working with this Task Force to generate responses to your generic questions. At a Task Force meeting on March 12 and 13,1980, the utilities present prepared and approved consesus responses to each of your generic questions. The Task Force further directed Westinghouse Electric Corporation to transmit these re-j sponses directly to you. The purpose of this letter is to transmit that information to you. It is our understanding that Mr. Wayne Stiede, Chairman of the Task Force, will also confirm to you by separate letter, the Task Force 4 decision to have Westing-house transmit these responses direct to you. We also understand that each utilit-y, in their specific response to your letter to that utility, will discuss the extent to which they agree with these consensus responses. If you have any questions on these, please contact'me. Sincerely, . M. Senmerling, h Dise Integrity Progra Manager oe: W. J. Ross, Operating Reactors Branch USNRC, Washington DC 20555 e r T / O ^ f-g. '. L' I- __a -a-Ls si / i,"

GENERIC QUESTIONS-TO BE COMPLETED IN 20 DAYS b 1. Describe what quality control and inspection procedures are used for the disc bore and keyways. ANSWER: Chemical analyses are made from each heat of steel. During manufacture mechanical tests are made from the disc bore region..These include tensile and Charpy v-notch impact tests. Each disc bore region is subject to ultrasonic and magnetic particle inspections. On later units, the disc keyways are inspected af ter machining, using liquid penetrant techniques. For in-service inspection two ultrasonic techniques, namely the tangential aim. and radial aim scans, have been developed to detect and determine the depth of dise keyway and bore cracks. The in-service ultrasonic inspection does not re-quire unshrinking discs from the rotor, The tangential aim scan is used to locate cracks. The technique requires sound energy to be coupled and directed tangentially towards the keyway from a precalculated position on tne hub. This is accomplished by means of a compound angled plexigalass wedge. The wedge is machined to provide a contoured face which makes complete contact with the dise hub, while alming the sound energy at the disc bore / keyway. Crack indications occuring in the vicinity of the key-way apex and at the bore will reflect the sound energy. The tangential aim scan is performed both in the clockwise and counterclockwise directions to permit locating crack indications with respect to the keyway apex. A radial aim technique is used to confirm cracks located by the tangential aim sean. The technique is also used to determine the crack depth by comparing the time lapsed in obtaining a ultrasonic reflection from the crack with the time to obtain a reflection from the keyway or bore. II. Provide details of the Westinghouse repair / replacement procedures for faulty

dises, ANSWER:

j When cracks are found by an inservice inspection their severity is evaluated by means of an allowable life calculation. The allowable life is relatable to the time required for the crack to grow to critical size for fracture. Based upon the results of this calculation, the following actions may be taken: A. If the affected dise has a calculated allowable life greater than zero a reinspection of the disc is recommended at approximately one-half of the allowable life, j len31 1

t B. If the affected dise has an allowable life less than or close to zero, one or more of the following may be employed: 1. The affected disc is removed by "machining", and is replaced with a collar and pressure drop baffle. 2. Upstream keyways may be drilled oversize to remove cracks after the downstream dbc b removed. 3. The affected dise may be replaced. This requires unstacking and restacking several discs on the rotor. III.A. What immediate and long term actions are being taken by Westinghouse to mini-mize future stress corrosion problems with turbine dises? ANSWER: The following short range actions are being taken: 1. Those discs which have been observed to be most susceptible to stress corrosion cracking are being redesigned. The new designs will achieve lower bore stresses and ut!!!ze lower yield strength material. These changes will increase the margin against stress corrosion cracking. 2. Designs that will eliminate spacers and bore keyways are being explored. The following long range solutions are being examined: 1. Bore Heating - Ways and means to keep the disc keyways dry are being explored. 2. Scaling - Ways of sealing the hub and bore from the steam environment are being studied. 3. Coatings - Another method of sealing is to apply a protective coating. We are continuing to experiment with different coatings, but extensive work is still required to develop processes for their application and to demonstrate their benefits. 4. Partial Integral Rotors - Since one piece forgings cannot be pro-cured at this time, we are exploring the possibilities of partial integral rotors where the first two or three discs are made a part of the shaft. Only the last few discs will have to be shrunk on. 5. Integral Rotors - A welded rotor design is being evaluated as a j means to procuee an integral rotor. len31 2

1 III.B. What actions are being recommended to utilities to minimize stress corrosion cracking? ANSWER:

• Westinghouse has developed recommended limits for steam purity. When these limits are exceeded corrective actions should be taken.

IV.A. Identify the impurities known to cause cracking in the low pressure turbines, and their sources. ANSWER: The mdn chemical species known to cause or contribute to stress corrosion of steam turbine materials in steam environments are: Sodium hydroxide Sodium chloride Sodium sulfate Oxygen 'Ihe sources of these impurities are under study. IV.B. Discuss the relationship between steam generator chemist.y and steam chemistry relative to the introduction of corrosive impurities into the turbine, including phosphate, AVT, and BWR chemistry. ANSWER: Analyses of material within LP disc cracks from PWR units shows the presence of Na, K, Ca, Si, C1, OH, and C together with Fe, Co, V, Al and Ni lons. I In PWR units with recirculating steam generators, the total carry-over of non-volatile dissolved solids, such as NaOH and Nacl depends mainly on the mechani-cal carry-over. However, where ammonia is used for pH control such as with the all volatile water treatment, carry-over of anions may increase due to a forma-tion of volatile ammonium salts. In the PWit units with once-through steam generators, the high pressure turbine steam purity is similar to the feedwater purity. Most impurities entering the steam generator ere carried directly into the turbine. The published information on BWR systems indicates the concentration of oxygen in the steam is in the range of 10 to 30 ppm. With respect to other elements, however, it is likely that high steam purity standards will be maintained for con-trol of radioactivity. To achieve this, BWR reactor water is generally double demineralized. IV.C. Discuss the mechanism of deposition of these impurities that can lead to their concentration in certain areas of keyways and bores. len31 3

t ANSWER: The impurities from steam can get into shrunk-on disc bores and keyways in sev- -eral possible ways:

• 1.

After deposition in the steam path during operation, corrodents can wash into disc keyways during layup due to moisture condensation. 2. In the wet steam regions, the moisture can dry on hot metal surfaces. 3. As long as the disc retains its shrink fit we are not aware of any mechanism which can concentrate impurities on the bore. V. What role does the refluxing action in the steam separation portion of the steam generator have on scrubbing corrosivo impurities from the steam? ANSWER: Two modes of transport of corrosive impurities from the steam generator to the turbine are mechanical entrainment and volatility. The non-volatile chemical species are transported by mecha' ical entrainment n which is normally expected to be small. The steam generator scrubbing equipment has minimum effectiveness in preven-ting the transport of volatile impurities, such as ammonium chloride, to the tur-bine. The concentration of volatile impurities in turbine steam is determined by their concentration in the steam generator bulk water and their specific volati-lity coefficient whleh differs with each species. VL To what extent can the buildup of corrosive impurities in the LP turbine be alle-viated? What would be the effects of the following action: A. Pumping moisture separator condensate to condenser? ANSWER: Pumping moisture separator condensate to the condenser would be beneficial in units with condensate polishing. In units without condensate polishing, there will be no effect. B. Periodically moving (the) point of condensation to prevent locallized buildup of corrosive impurities. ANSWER: Conceptually, dilution of contaminants by increased levels of moisture and their subsequent transport to the condensate system could substantially reduce the buildup of impurities. However, the effectiveness of this technique and the means for successful control of the local environment of particular turbine parts i must be developed and experimentally verified, len31 4

/ Several of the less volatile active corrodants, such as sodium chloride and sodium sulphate precipitate as concentrated liquid solutions in a region slightly above the equilibrium saturated vapor line of pure water. This region occurs locally .within a given stage during normal operation and migrates toward the turbine ' exhaust as load reduces. Control of the zone can be affected by changes in load j

• and moisture separator reheater (MSR) outlet temperature.

i l VII Describe fabrication and heat treatment sequence for dises, including thermal exposure during shrinking operation. ANSWER: 4 The typical sequence for producing a dise forging includes the following opera-tions, not all of which are necessarily applicable to any given disc. A. Melting and casting of Ingot. Most discs manufactured since the early 1960's are made using basic electric furnace steel whleh is vacuum stream degassed or vacuum-carbon-deoxidized. B. Forring The ingot is heated to forging temperature, block forged and cut into 2 to 4 pieces from which the Individual disc forgings are made. l C. Preliminary Heat Treatment This step consists of austenitizing and temper-ing the forging to promote structure uniformity, grain refinement, and good machineability. D. Preliminary Machining The forging is machined to the dise contcar. E. Preliminarv Ultrasonic Inspection Typically the supplier makes a partial ultrasonic inspection of the forging to assure that the quality warrants continued manufacturing effort, s i F. Heat Treatment for Properties The forging is austenitized and tempered at appropriate temperatures to achieve the desired mechanical properties. Cooling from the austenitizing treatment is achieved by water quenching. After temper-ing the forging is cooled in the furnace at a controlled rate. ) G. Mechanleal Properties Tensile properties are tested to determine if the re-j quired strength level has been achieved. Since about 1960, Charpy v-notch im-pact tests are made on each forging. q I H. NDE Inspection The forgings are rough machined to the Westinghouse draw-l ing requirements and an ultrasonic inspection of the flat surfaces of the hub, web, and rim of the disc is performed. a L Stress Relief This treatment is required when a significant amount of metalis machined off of the forgng after it has been heat treated for properties. The stress relief treatment a ~0-1000 F below the tempering temperature. Cooling is accomplished by a ey = clied furnace cool. J. Mechanleal Properties When a stress relief is used, the mechanical properties 1 are tested after the stress relief treatment. (Reference Step G) J j l len31 5 i

/ K. Dimensional Check The forging is machined to a clean surface, the balance of test prolongations are removed, and the dimensions checked. The forging is then shipped to Westinghouse for final machining and assembly onto the rotor. ' L. NDE Inspection A fluorescent magnetle ~ particle inspection is performed

• af ter finish machining (This inspection was not applied during the early 1970's.)

~ M. Shrinking Discs On the Rotor Shaft The assembly operation consists of four parts; namely, preparation of the shaf t, preparation of the dises, assembly of the rotor and pinning of the discs to the shaft. 1. Preparation of the Shaft After final shaft machining and inspec-tions are complete the shaft is cleaned with degreaser and dry lint-free cloths, and is mounted in a vertical position. The surface of the rotor that will be in contact with the disc is coated with lubricant. 2. Preparation of the Disc. After final machining and inspections' are complete the disc surfaces and blades are cleaned to remove foreign material. Prior to heating for assembly the disc bore diameter is measured and compared to that of the drawing to assure a correct shrink fit. The disc is placed on an assembly fLiture, leveled and loaded into a furnace which is at 300 F or 0 less. 3. Assembly of the Rotor The disc is slowly heated to the required 0 0 shrink temperature between 600 and 750 F. When the shrink temperature is reached the disc is removed from the furnace and lowered onto the shaft. 4. Axial Aligning and Pinning of Dises. Liners are placed at the exhaust face of each disc to assure the proper axiallocation. The keyways are then drilled. Since the early 1970's, a penetrant in-spection is performed in the keyway prior to inserting the key. VIII Discuss the effect of any local residual stresses on the cracking mechanism. ANSWER: Depending on their nature and magnitude, residual surface stresses can have an effect on crack initiation. Proper control exercised in the selection of machining parameters re:;ults in compressive stresses which are usually beneficial At the apex of the keyway, the residual stresses may be influenced by local yielding as a result of the stress concentrating action of the keyway. 1 len31 6

.(:., ENCLOSUPI 5 Appendix B (Non-proprietary) 4

8 A h SITE SPECIFIC GENERAL QUESTIONS I. Provide the following information for each LP turbine: A. Turbine type San Onofre Unit 1 utilizes one tandem compound four flow, three casings, condensing,1800 RPM turbine utilizing 40 in. last row blades in each low pressure element. The low pressure element is designated as a Building Block 80. 2. Number of hours of operation for each Lr turbine at time of last turbine inspection or if not inspected, postulated to turbine inspection. The total number of operating hours until the scheduled Spring 1980 refueling cutage is 80,725 hours. Th6.s is based upon the cumulative hours reported in the Janrary, 1980 monthly report plus 100% operation time between February 1, 1980 and April 11, 1980. C. Number of turbine trips and overspeeds There have been seventeen reactor trips (resulting in a turbine trip) and eight turbine trips from approximately 205 power or higher. Since there are no intercept valves on the low pressure turbines, each of these trips resulted in an overspeed condition l (greater than 100% speed). D. For each disc 1. Type of material including material specifications The type of material is Ni-Cr-Mo-V alloy steel similar to ASTM A-471. The minimum yield strength specified for each disc is given in Table 1, Section B. l 2. Tensile properties data Tensile properties data of tests taken from the dise hub are given in Section B of Table 1. Data obtained from rim material are presented in Section C of Table 1. 3 Toughness properties data including Fracture Appearance Transition Temperature and upper energy and temperature. Toughness data are presented in Table 1. Data fer hub material are in Section 2 and data for rim materiel are in Section C. Upper shelf energy is not presented when it is the same as the room temperature energy.

N 4 Keyway temperatures Hub operating temperatures are listed in Section G of Table 1. This is the calculated temperature 2" from the exhaust face of the disc at the bore during full load operation with all moisture separator reheaters functioning. 5. Calculated keyway crack size for turbine time specified in "B" above The calculated keyway crack size at the end of April 11, 1980 (the scheduled start of the Spring 1980 refueling outage) is shown in Section G of Table 1. The crack size is calculated by multiplying the estimated maximum crack growth rate by the operating hours in I.B. The estimated crack growth rate and calculated crack size for disc 6 for each low pressure turbine is zero since that disc operates dry. Disc 1 operates dry because of the heat added by the moisture separator reheat-era, which operate approximately 95% of the time. Disc 6 operates dry because of the additional heat added by the turbine sealing steam. 6. Critical crack size The calculated critical crack size for each disc is listed in Section F of Table 1. I l 7. Ratio of calculated crack to critical crack size The ratios of calculated crack to critical crack size are given in Section G of Table 1. 6. Crack growth rate The crack growth rate for each disc is listed in Section G of Table 1. 9 Calculated bore and keyway stress at operating design overspeed The bore tangential stress at 1800 rpm and 2305 rpe (1285) are presented in Section E of Table 1. The values presented include the stresses due to shrink fit and centrifugal force loads only. Additional analyses to include thermal and pressure stresses are being made, but are not presently available. Keyway stresses vary with location in the keyway and approach 90% of the yield strength. 10. Calculated Kje data The fracture toughness of each disc is preserted in Sections B and C of Table 1. Kje is calculated frem charpy V-notch and tensile data. The values presented are at the upper shelf temperature or reem temperature, whichever gives the icwer i result.

o , 11. Minimum yield strength specified for each disc The minimus yield strength specified for each disc is presented in Section B of Table 1. II. Provide details of the results of any completed inservice inspection of LP turbine rotors, including areas examined, since issuance of an operating license. For each indication detected, provide details of the location of the crack, its orientation, and size. Inspection dates and results for the No. 1 low pressure turbine (north) Gre listed below. December, 1966 Investigation revealed that 9th stage 'slades in the low pressure turbines had lower than desica frequencies. The blade shroud was machined and underwelded to raise the frequency. July, 1967 There was blading failure in the south (11th) stage; 56 blades were broken or damaged. Four additional blades were found cracked, one of which was in the north end. The entire 11th stage blading in both ends of the #1 L.P. were replaced with blading of a different design (400 blades). i June, 1969 During the overhaul inspection of the turbine / generator, a crack was found in the root of blade f 51, L-1 stage, generator end of the #1 L.P. A total of 13 blades were replaced. Several low pressure turbine blades were removed from #1 L.P. due to cracking adjacent to the tie bar. Analysis showed the cracking was due to forging defects. Erosion damage was found in last two stages of both L.P.'s and i I diffusers. There are records of repairs. February,1970 The tith stage blading of both L.P.'s were inspected for erosion. No excessive erosion was observed. June, 1973 The back end of last stage of #1 L.P. turbine were magnaglowed. No cracks were found. October, 1973 A turbine vibration alarm on the No. 4 bearing of the #1 low pressure turbine was received at 11:52 p.m. on l October 30, 1973 The unit was operating at 450 MWe gross. A gradual load decrease was cccmenced and the turbine was removed from service.

m -4 Entry was made into the No. 1 turbine exhaust hood and a preliminary inspection revealed major impact damage to the last stage rotating blades on the generator end of the #1 L.P. turbine. After removing the exhaust hood and the No. 1 inner cylinder a more detailed inspection was performed. Two blades in the L-1 stage, generator end were found to have failed: No. 41 at the root and No.16 at the base of the stellite erosion sh' eld. Both these failures were deter-mined by Westinghouse to have been caused by fatigue. The No.1 inner cylinder and inner blade rings were removed a'nd the spindle was pulled for repairs. The entire spindle was blasted and the blade roots and steeple area on each wheel were magnaglow inspected. This inspection resulted in finding four blades in the L-4 stage, governor end, with root cracks: Nos. 42, 48, 78 and 192. Each of these blades was the trailing blade in its group of six and each was cracked on the inlet side. Also found was a root crack in blade No. 201 of the L-1 stage generator end. This blade was a replacement for blade No. 51 which haj failed in the same manner in 1969. The last stage blading was removed from the generator end along with the L-1 blade groups damaged beyond repair and the four grcups frem the L-4 stage governor end. After cleaning the steeples in the area of the removed blades, a crack was found in the outlet side of the steeple between blade Nos.196 and 197 on the L-1 stage generator end. The L and L-1 stages, generator end, and the L-4 stage governor end steeples were glass bead blasted, a process t by which the steeples can be cleaned without damaging the serrations. No additional steeple cracking was found. The renSinder of the L-1 blades were removed frem the generator end and all the L-1 and last stage blade roots and steeples were glass bead blasted and checked. This inspection uncovered root cracks in blade Nos. 42, 76, 119, 149, 196 and the original 201 in the L-1 etage and Nos. 160 and 168 in the last stage. All cracks were determined to be the result of fatigue. The cracked steeple between blade Nos.196 and 197 of the L-1 wheel was removed and a bridge block was inserted in its place. To maintain proper balance, the steeple on the opposite side of the wheel (between blade Nos. 97 and

95) was removed and a similar bridae bicek was put in its l

lace.

l 1

B h l The last stage blading (200 blades) was entirely replaced with new 17-4 PH blades. In the L-1 row,129 new blades were installed; 97 blades of 121 Cr. and 32 blades of 17-4 PH. Seventy-three 121 Cr. bledes were salvaged from the original L-1 blading and we-o reinstalled. Four blades were not installed due to the removal of the two steeples for the bridge block inserts. March, 1975 The No. 1 L.P. turbine rotor was removed, cleaned and inspected for blade root and tenon cracking. Several minor tenon cracks were ground out but no root cracks were found. The spindle was removed and cleaned for inspection. Several tenon cracks were found but no evidence of cracking in the root area or the steeples was noted. Indications observed on the L-2 stage tenons, blade No. 85 generator end and No. 26 governor end did not require removal due to the underwelded shroud. June, 1976 The No. 1 L.P. was dismantled, the rotor sandblasted and NDT inspected for defects. Several tenon heads had small crack indications which were polished out. Several welds on the L-4 stage harmonic shrouds were found to have lack of fusion and needed general clean-up. April, 1978 The outer steam gland seal rings and all outer oil seals were replaced during this outage. Inspection dates and results for the No. 2 low pressure turbine (south) are listed below. December,1966 Investigation revealed that 9th stage blades of the low pressure turbines had lower than design frequencies. Blade shroud was machined and underwelded to raise the frequency. July, 1967 As a result of the blading failures in the #1 L.P., the entire 11th stage blading in both ends of the #2 L.P. was also replaced as a precautionary sensure. (400 blades) June, 1969 During an overhaul inspection of the turbine 6enerator, it was necessary to replace two blades in the #2 L.P. Erosion damage found in last two stages in both L.P.'s and the diffusers. No record of repairs. February,1970 tith stage blading of both L.P.'s inspected for erosion. No excessive erosien observed. Bisdes 63 through 66 en generator end of #2 L.P. observed loose. Ceneluded that bledes would tighten when turbine heated up.

, No. 2 L.P. turbine was also disassembled end inspected. No blade cracking was found. Several miner tenon cracks were found. These were polished out and the turbine was reassembled. June, 1973 Back ends of the last stage of #2 L.P. magnaglowed, revealing root cracks in two blades. Two groups (8 blades) were replaced. March, 1975 The No. 2 L.P. turbine was inspected in place. One blade in the last stage generator end was found to have a cracked root. The four blade group containing this blade was replaced. Blade No. 162 in the L stage generator end was found to have a 3/16" crack in the upper serration of the root on the trailing edge. This is the leading blade in a group of four (156 through 162). All four blades were changed and the lashing wire welds shot peened. Locktite was used on all blades in this stage. June, 1976 The No. 2 L.P. was dismantled, the rotor sandblasted and NDT inspected for cracks. Conditions on disassembly were as follows: A. Very heavy erosion on inlet end of "L" row blades both governor and generator end. B. Many blades chipped on the trailing edge where they ride against shroud approximately 1/4" into blade and 1/2" down. C. Several cracks on both governor and generator tenon heads. D. Lost tip of blade #120 generator end - group 120, 121, 122, 123, 124 (L-1 row). S. Very heavy cut in #1 inner cylinder cover on L-1 stationary generator end. Several nicks also on L-1 and L stationary. F. Horizontal steam cuts on both #1 and #2 inner cylinder covers. G. L-1 seal strip on generator end bent over. November,1976 Recommer.dation that at least one row of 40" blades be refurbished by gas welded stellite program during 1978 refueling.

M April,1978 L.P. #2 was opened, as erosion was known to be more advanced on that turbine. Six leading blades were examined on each end, accessibility being limited because the unit was not on turning gear. The trailing side of about 24 blade roots on each end were also Tisually examined. No defects were found in the roots. Erosion damage varied form blade to blade ran61ng from 3/16" to 5/16" deep and averaging about 1/4" deep at the base of the 8" stellites. There was no erosion at the base of the 16" stellites, but notches near the tip had already occurred in these more recently installed stellites. (Original blades have 8" stellites - replace-ments have 16" stellites.) September,1978 N.D.T. of turbine components revealed evidence of physical damage. Results of that inspection are listed below. LPA TURBINE ROTOR TURBINE END A. L Stage 1. Visuni and Liouid Penetrant Examination: Inner Lashing Lugs - Moderate physical damage. Grind mark between Blade #111 and #112, 1/4" x 1/16". Center Lashing Lugs - No indication of defects. Outer Lashing Lugs - Crack indications as follows: Between Blade #17 and #18 - 1/2"; between Blade #199 and f200 - 3/8"; between Blade #185 and #186 - 3/8"; between Blade #182 and #183 - 1/4"; between Blade #181 and #182 - 1/4"; between Blade #178 and #179 - three, 1/4"; between Blade #170 and #171 - 1/4"; between Blade #167 and #168 - 1/4"; between Blade #166 and #167 - two,1/4"; between Blade #165 and #166 - 1/2". Blades - Minor physical dama6e and major erosion (see drawing). Blade #136 - Minor physical damage (derit) 1/8" x 1/2", discharge side.

M Dise-to-blade - Moderate erosion to disc and blade (see drawing). GENERATOR END A. L Stage 1. Visual. Magnetic Particle. and Lieuld Penetrant Examination: Inner Lashing Lugs - No indication of defects. Center Lashing Lugs - Crack indication between Blade #107 and #106 - 1/4". Major pitting between Blade #101 and #102 - 1/8" x 3/16". Outer Lashing Lugs - No indication of defects. Blades - Minor erosion at tip of blade adjacent to stellite (length of stellite - 16 1/2"). Moderace physical damage to Blade #179 - 1/2" x 1/4". Disc-to-blade - Moderate erosion (see sketch). NOTE: All indications on lashing lugs were repaired, reinspected - No indication of defects were noted. LPB TURBINE ROTOR TURBINE END A. L Stage 1. 11gyal. Magnetic Particle. and Lienid Penetrant Examination: Inner Lashing Lugs - No indication of defects. Center Lashing Lugs - No indication of defects. Outer Lashing Lugs - Crack indication between Blade f175 and #176 - 3/8". Major pitting between Blade #169 and #170 - 1/8".

= h Blades - Major erosion (see sketch). Blade #86 - Minor physical damage (dent), 1/8" x 2", discharge side. Blade #57 - Hinor physical damage (dent), 1/8" x 2", discharge side. Blades - Blade #19 - Minor physical damage (dent),1/2" x 1/4", adjacent to inner lashing lug, discharge side. Blade #11 - Minor physical damage (dent), 1/2" x 1/4", adjacent to inner lashing lug, discharge side. Disc-to-blade - Moderate erosion (see sketch). GENERATOR END A. L Stage 1. Visual. Magnetic Particle. and Liould Penetrant Examination: Inner Lashing Lugs - Major debris between Blade #125 and 0126 - 1/4" x 1/4". Center Lashing Lugs - Major pitting between Blade #129 and #130 in line porosity - 1/4". Major pitting between Blade #177 and #178 in line porosity - 1/4". Crack indication between Blade #44 and

1. 45 - 1/4".

Crack indication between Blade #165 and

1. 166 - 1/4".

Outer Lashings Lugs - Incomplete weld between Blade #99 and #100. Major pitting (hole) between Blade #132 and

1. 133 - 1/8" x 1/16".

Blades - Major erosion (see sketches). Blade #178 - Major physical damage - torn,1/8"; dent - 1/4" x 1/8". Blade #187 - Major physical damage - torn,1/8"; dent - 1/4" x 1/8". Blade #71 - Minor physical damage (dent), 1/4 " x 1/16". Blade #67 - Major physical damage (torn). Blade #38 - Moderate physical damage l (dent). 1/4" x 3/8". Blade 8145 - Mcderate physical damage - gent stellite,1/2" x 1/8" adjacent to j outer lasning lug. I )

e N Blade #165 - Major physical damage (tear), 1/8" long and dent, 3/4" x 1/4". Blade #171 - Moderate physical damage (dent),1/4" x 1/8", adjacent to center lashing lug. Blade #172 - Major physical damage (tear),1/16" long and dent,1/8" x 1/4". III. Provide the nominal water chemistry conditions for each L.P. turbine and describe any condenser inleakages or other significant changes in secondary water chemistry to this point in its operating life. Discuss the occurrence of cracks in any given turbine as related to history of secondary water chemistry in the unit. Nominal water chemistry for both low pressure turbines at San Onofre Unit 1 is reflected by the chemical limits for steam and condensate pump discharge as specified in Station Order S-E-2. These limits are listed below. Unit 1 Limits of Chemical Concentrations Steam: Chloride 0.15 ppm (maximum) Silica 0.02 ppm (maximum) Sodium Carryover 0.25% (maximum) Condensate Pump Discharge: pH 8.8 to 9.4 (range) Conductivity @ 250C 6.5 pahos (maximum) Cation Conductivity 0.5 pmhos (maximum) Dissolved Oxygen 7.0 ppb (maximum) Ammonia, (NH ) 1.0 ppm (maximum) 3 Iron, (Fe) 10 ppb (maximum) Copper, (Cu) 10 ppm (maximum) Chlorides 0.5 ppm (maximum) Condenser inleakage occurred primarily during the years 1971-73, in which approximately 65 of the tubes were plugged, largely due to inlet end erosion. In June-July, 1973 one quarter of the condenser was retubed, and the remainder of the condenser was retubed in March-April, 1975. Significant improvements in corrosion-erosion resistance of the tubing were incorporated. Since the retubing, inleakage has been essentially zero. No cracks have been detected in the turbine rotor or blading which were attributed to adverse secondary water chemistry. IV. If your plant has not been inspected, describe your proposed schedule and approach to ensure that turbine crackins does not exist in your turbine.

_ Each low pressure turbine disc will be ultrasonically inspected in the keyway and bore area during the Spring, 1980 refueling outage. The outage is currently scheduled to commence April 11, with turbine inspection work commencing approximately April 15, 1980. V. If your plant has been inspected and plans to return or has returned to power with cracks, provide your proposed schedule for the next turbine inspection and the basis for this inspection schedule. The San Onofre Unit 1 low pressure turbines have not been inspected. VI. Indicate whether an analysis and evaluation regarding turbine missiles have been performed for your plant and provided to the staff. If such an analysis and evaluation has been performed and reported, please provide appropriate references to the available documentation. In the event that such studies have not been made, consideration should be given to scheduling such an action. i 1 1 An evaluation regarding turbine missiles has been performed as part of the NRC's Systematic Evaluation Program (SEP). The results of this evaluation are documented in the NRC's draft topic assessment for SEP Topic III.4-B, Turbine Missiles, forwarded by your letter of January 5, 1979. The conclusion of that assessment was that the overall probability (3 x 10-7 per year) of turbine missiles damaging the plant and leading to consequences in excess of the 10CFR Part 100 exposure guidelines is acceptably low. i k i I

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8. MAlfRIAL PROPERTIES (MuB3 C. MATERIAL PROPERTIES TRIM 3

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EIC

11. U.S. MICtuSI+50RTII=.38

-(K5I+50RiiIN.33 D. CHfMISTRY b 51 b P b CR b b W b E -3 ,C e E 3 ,c. c E =3.c.e C "3.C,8 E ~1 ,C,C. EMO~1.C,E..._C l ,C,C C b Ma n b 58 6 5-6 cu 6 g > -y.c.e 7 3.c.e g 3.c.e g 3.e.e g b.e.e g p.c..e-g.... 7.e,e E. BORE STRESS F. CRACM DAT) ___ SP([0 (RPMt SIR [5s h,e g 4 g 1. 3a00 EASIB y 1. A-CR-OP (1800 RPMI (IN.1

2. A-CR-05 E0VERSPEEDI._11N.J.

2. 2305 412448 tmSIl

,j G. SERWICE DATA ,be ~ - e 1. OPER. TEMP, 41[IAL II.ttP..itta aMn_rt, 2. Eatimaied man dA/JT (In/!!r) 3. Calculated man crack alze (In) 4. Ratio of calculated to critical crack mise g e_. 0

I dla 1 (6 Led & 4 24) TOf k% C h6L )A OL ~ Wdigkoose Trogy'idug ID e : 0080801001 LP TURBINE DISC INFORMATION A. UNIT IDENTIFICA1 ION

8. MATERIAL PROPERTIES eMuBI C. MATERIAL PROPERTIES (RIMI

}DAC 1. tsu1LDING 6LOCm 60 3. svPE la (MSIIB (MIN. V.5. 2. UNIl SAN ONOFRE a3 2. SUPPLIER: DvALL HEPP J5 TALL _ M C,C., __,_tuSI3. _ _ _ - h,6, (

3. Cuit oME R:

50. CALIF. ED.

3. v.5. SusIn 3. v.5. m. LPa 1 9. U.T.5. 4K513 r-

2. U.T.S.

ENSIS

5. LOCAIION GOW

5. ELONGATION l

3. ELONG ATION 6.

DISCS 6 61. R.A. ~

5. F A T I 't DE G.f* f 4,

R.A 7. 1E5I NO. 1C82299 7. FATT GDEG.F3 6. R.T. IMPACitFT.L8.3

8. R.I.

IMPACitFT.LB.3 9. U.S. IMPACT TEMP. 'I. I. U.S. IMPACT TEMP. ' ~ t DE G.F 3 U.S.' IMPACT,F3ENG. 8D[G

10. U.S.

IMPACT ENG. S. ",.1 4FI.LB.3 4FI.L8.3 II. U.S. RIC

9. U.S.

MIC (M51*5QRitIN.Il (K5It50RitIN.la

o. C rMIsiRv P

6 CR b C b MN b 53 6 MO b V 6 t 1 .c. c 0 3.c.e E - 3.c.c C _. G.c.c C 3.c. c C 7,c,c E 3,c.e b ^5 b 58 L $N AL Cu L y 6 E "I 7,c,c L 3,c.c E 7,e,e C 3 ,c, c_ f3f t,e. C ~\\,c,e_E, ~3,c,e E. 60RE SIRE 55 F. CRACM OATA ' ' ' ~ - - - - ~ ~ ~ h,cg SPEED tRPM3 STRESS 3. 1800 cmSI) 1. A-CR-OP (1800 RPM 3 (IN.3

2. 2305 412848 EM513

2. A-CR-05 40VERSPEE03 ( I N. 3,.

v., 6. 51RWICE DAIA 1. OPER. IEMP. MEigt IEMP. HUB (DEG.F 3 2. Estimat=J m.au JA/JT ( t a /ll r ) 3. Calcislated man crack size (In) 4. Itat to of calculated to critical crack mise s g m l I 4

TaWe t (. %c+ 7 x 24) ro. w e hh C M OUSC (O 4C M ID a : 038 D IG I t.0 2 LP tuRetNE DISC INFORMATION

8. MATERIAL PROP (RTIES 4HuBe C. MallRIAL PROPERil[5 (RIMS 8

TB A. Uhli IDENIIFICAIION ~ b((MSIII b.C t'

1. bull 0thG BLOCm 80 1.

EYPE e EMIN. Y.5. ' }. A.T., ~T-1-

2. UNIT saa. ON0fRE 81

2. SUPPLIER:

n DWAL HEPPLNSTALL 1. Y.5. 4M51)

3. CuSIOMER:

10. CALIF. EO.

3. v.5. (N51)

2. U.T.S.

(K518 !+ 3 4. U.1.5. tuilt .g.

3. FLONGATION 5.

40 CATION 6E n

5. CLONGATION d

4 LPs t 4 R.A. L. O!5Ce 1 6. R.A. . ?

5. FATI EDE G.F s

7. FAIT 8 00 G.F 8 4

6. R.I. IMPACT 4FT.L8.3 T. 18 51 No. 1089744

8. R.I. IMPACitFT.LB.)

'. l s;

7. U.S. IMPAC1 1[MP.

9. U.S. IMPACT TEMP. 40EG.f 8 tDEG.F3 t' (F!.LB.3

10. u.5. IMPACI (NG.

~

8. U.S.. IMPAFI ENG.

(FI.LB.I II. U.S. alc

• W.

9. U.S. MIC ,;~~wd in5!*SQRT(IN.88 .(fL51oSQRI(I N. 3 3 6 b no b b (C -],c.t (M* 3.c.e ( 51 )b,c.e E 3,c,e [Ca 3,c.e E 3.c.e.(v 3 ,c, e D. ChtMISTRY p b t S ~ bA A5 L 6 58s b AL b Eu b s b C=l 3 .C E 3,c,e E. 58 3,c,e. C ~1,c, te C 7.c,e E 3,C,c.__ E 3 ,c,e F. CRACM OATA

f. 80Rf SIRf55 g

SPEED (RPM 8 51Rf55 _gg

3. A -C R-OP (1800 RPMS tlN.3 1.

1800 (M518

2. A-CR-05 80VERSPEED) (INet.

g

2. 2305 (12das taill

- h.c, e

6. 5fRwlCE OATA

l. OPfa. IrMP. ME1*L IEnP. hub _lDEG.F3 2.

Estimated'ska JA/E8 ( I n /tt r ) 3. Calculated man crm k size (In) 4. satto of calculat I to emitical crack size e e a L

,s ~ T a le ( 6tu+ r 4 20 'Tu, Re. h Dara. LP IURBINI DISC INTORMATIOk A. UNII IDENTIFICATION B. MATERIAL PROPERTIES (HUB) C. MAT [ RIAL' PROPERTIES TRIM 3 I. BulLDIh6 BLOCN 80 1. IvP[ eye, C, gg (MIN. V.5. GNSI3t

2. Und I I SAh ONOFRf a1

2. SUPPLIER:

WAL 3. CU$tOMf R:

50. CALIF. [0.

3. Y.5. (K518 h HE PPQtsT ALL ,I.C.C ' b.Os t', 4 LPs 1 4 U.T.5. ENSI3 1. V.S. (KSIS

5. LOCAIION 6t h 5.

ELONGATION

2. U.T.5.

8M5Il

3. ELONGATION NO.

TC73865 I I (DEG.F8 ~ - ~ " I i'80f6.F3 ~ ~

4. R.T. IMPAC18FT.L8.3 6.

R.I. IMPACitFT.L8.3 9. U.S. IMPACI TCMP. T. U.S. IMPACT TEMP. 4DEG.F3 ~0. U.S. IMPACT ENG. (Df$.fi SFI.L8.8 4.'u~ C IMPACI [4G. -- ~ ~ ~ t

31. U.S. KIC 4FT.L8.8

9. U.S. MIC (N54*10RT(1N.9)

L D. CHEMISTRY __jlLSIosQRIgIN.jj j C b tik b 5I h b L 3,c,e L 3.c,C C 3.C,C C 3.C, C C 3,C.S,CM0 1bg,(* T 7 C C"- p ga b V h gi s.c.c g g.c.e g 3.C.c b e.e At A5 58 s $= y , c, e. .e, s 6, c, e _ _. _ _. E. BONE STRESS SPEED s @M 3 STRESS 3. 3800 (mill _ (q - F. CRACM OATA f~

2. 2305 (I2atl

$KSI)

1. A-CR-OP (1800 RPM 3 (IN.)

2..A-CR-05 (Oy[R$ PEE 03.04.),

G. SERrICE DATA b.C f.

1. OPER. IfMP. ftLIAL JittE, HpB 40EG.fp 2.

Estlawted man JAfdf (In/lir J 3. Calculated man ca ack maze (Isa) 4. katto of calculated to critical crack size +ee., 6ee = m Ne.ge e . - ~..

v. T a le 1 ( skeet 9 a 24) 'Tt,< % e bisc. Tcha Wes4igbost wo erichg 10 e : 00a 01 C 4 4,02 LP IUR8INE DISC INFORMATI0h A. UNII 10tNilflCATIch B. HalfRIAL PROPERilES (HUB 3 C. MATERIAL PROP [Ril[5 TRIM)

1. bulLDIAG 6LOCm e0 1.

IvPt 3.c. t: T8 EMIN. v.5. taillt ~ 6 c* g MEPPrN5 TALL Ib 8. t' _ (MSIs 1. UkII 5AN ONOFRf 81 SUPPLIERt M OWAL 3. CuS IOME R:

50. CALIF. (O.

v.5. En5It 1. v.5. 4 ipa 4. U.i.5. (NSIB

2. U.T.S.

(MSI) 5. td:a:Ich Gt N

5. fLOhGATION

3. ELONGATION to bl5t e 3

6 R.A. 4 R.A. 7. If 51 NO. IC89fb7 7. FAli (DEG.Fl

5. FATI IDEG.F3 8.

R.T. IMPACitFI.LB.3 6. R.T. IMPACitFI.L8.3 9. U.S. IMPaCI 1[MP.

7. U.S.

IMPACT TEMP. (OfG.F) (DEG.F3 10. U.S. IMPACT ENG.

8. U.S.. IMPACT [NG.

IFI.LS.8 (FI.LB.3 II. U.S. MIC 9. U.S. KIC ENSI*10RIIINell (N51*SQRitIN.38 D. CutnlinRv F U M 6 5 .e, e 6e.e CR 6 HD 6 v o C J.e.e C 1.c.c C1 C.e 3 C 1.e.c E 1 ,e.e C 3.e.e g 3 g 3.c.e 58 y.e,c Ni be, e A5 b SN c.c.c At 3.e.e e cu 6.c. e 5

6. e, e

t. BORT Stkf55 F. CRACM OATA

~ h4d SPE E D (RPM 8 519055 h 1. 1800 in5Il

1. A-CR-OP (1800 RPM 3 alN.B 2.

2305 812sta (MSIS

2. A-CR-05 (OWERSPE(08 EIN.)

f.. SERWICE DalA h.c.e -

1. OPER. IfMP. HE I Al. IE MP)ti r at 1!}{S.F 3 (In 2.

tutinated man JA/JT 3. Calculated ama crack slze (In) 4. Ratio of calculated to critical crack alze

g l' Table 1 (.Skat to 4 24) W ht l C 4 uks+A 6 w Trogriebg 3D e : 0080101602 LP TuRBIh[ DISC INFORMATION A. UNIE IDE N T IF I C A T ION

8. Mal [ RIAL PROPERTIES (Hues C. M AT ER I AL"PROPE RT IE S TRIM 1.

b u ! L D I ht. SLOCs 80 1. TYPE a. C. C., 18 p (. suSIll .--l b.C,( M A UW AL]L EMIN. v.5. t. uns I T Sah h0F R[ el 2. SUPPL IE R : MCPPENSTALL h 4 C

3. CuitoMER:

50. CALIF. [0.

3. V.S. (N518 f I. Y.5. (K5Il_ _, ,e 4 EPs I 4 U.f.5. (MSIS

2. U.T.S.

tW5Il S. t ot A TION G[ N 5. flokGATION

3. ELONGATION t.

(. t S t a 4 6. R.A. 4.,R.A. -tOf GJ)~ F. If 5I hu. 1C82287

7. FATT 50EG.F8

5. FATI

8. R.T.

IMPACidFI.LB.3 6. R.T. IMPACitFI.LB.3 9. u.5. IMPACT TEMP.

7. U.S.

IMPACT TEMP. 40EG.F3 8 ~ 60[G fi ~ ."U.5.~ IMPACT.ENG.

10. U.S.

IMPACT ENG. (FI.LB.3 (FT.L8.1 II. U.S. MIC

9. U.S. MIC (M51*50RitIN.la

._,_jn51950RitIN.II D. CMEMI5ikv Mu b Si b e bs CR b v 6 c k z,e t 1 c 3.e,e E 3,c,c E -3 ,e C 3.c,c c MO ~1,cd c 3 ce b A5 b 5a b AL 8 Cu b 1 bcc L* 3,c, e E 3.e,e E 3,c,e [SN ]b,c, e f ~1,,c,e E 7,c.c_C ~1., - E. 80Rt STRESS F. CRACM DATA SP((D (RPMB STRE55 gg }. 3600 Insis I. A-CR-OP (1800 RPM 3 (IN.I I. 23G5 tilati taill j

2. A-CR-05 10vfR5P[(Qi_jipfel

f.. SERwlCE Data

( C, t v.

1. OPER. 1[MP. MC]AL If MP, ttu8 JQLia.f 3-..

2. EstimatcJ man JA/JT (lu/lir'l 3. Calculated man crack size (In) ~- 4. Ratio of calculated to critical crack of,e ~ ~ m e a

i A le n ( 5 Luf n of 24) W M l% 646pm. fr g vie 4*g ID a z D080308602 LP IuRBINE DISC INF01MATION A. 0418 IDENTIFICATION B. MATERIAL PROPERTIES thuBI C. MA TERI AL PROPERT![5 ERIM3

3. BUILDING 6LOCm a0 3.

IYPE 'p.f. f-T8 iMik. v.5. taill)

2. oh!T SAh ONOFR[ s!

I. SUPPLIERz f1 WAL HEPP Q5 FALL,[$.C.C .(M519_ _ _ _ I-b. C.(3 3. CuiluMERI

50. CALIF. ED.

3. v.i. (N519 4 LPs 1

4. U.T.S.

(MSIS 1. V.S.

5. LOCATION 6(N

5. fLONGAIION

2. U.T.S.

SMSI)

6. O!50s 5

6. R.A

3. flokGAIION 7.

If 53 h0. TC82292

7. FAII IDEG.F3 q.

R.A.

5. FATI IDt6.F3

8. R.I.

IMPACitFT.LB.! 6. R.T. IMPACitFI.LB.3 9. U.S. 3MPACI TEMP.

7. U.S.

IMPACI TEMP. 8 0CG.F 3 IDEG.F3

10. U.S. IMPACI EhG.

8. U.S._ IMPACT ENG.

IFI.L8.8 (F1.LB.) II. U.S. EIC

9. U.S.

MIC tM5I*50RIIIN.I3 j, (K51+1QRTIIN.38 O. CH&MISIRT C Ar MA lo Si b P b FR h NO b y b L 3 .c,C. E 3 .c,C. E 1, t, C. c 3 ,C,C C 3,C, e C 3 ,c, C_ __C 3, c, C p > 3.c.e g 3,.e,e g p.e.e. g - C f' f '"3 ''" ~ ~f P * ~- 6 A5 i 58 5 u.e. e E. 80Rf SIR [SS F. CRACM OATA SPflD tRPMS SIRESS Qc 3. 3800 in518

2. 2305 412sta taila

1. A-CR-OP E1800 RPM 3 IIk.5 I

] g

2. A-CR-05 80VERSPEE01 IIN.1____

[ ] 6. SERVICE DATA 1,.e, e

1. OPiR. IfMP. MfIAL ILMP. maa a m. _ r a.

2. Est imeteJ ama dA/d7 (lu/llr ) 3. Calculated man crack asse (In) 4. Barto f calculated to (ritical crack size

T We n ( sLee+

12..f 2 4 )

'L bde ~Dde hk hf, 4 9 FO{ f

• O 10 e : DO A 010 ! a>02 LP IURblNE DISC IhFORMATION A. UNIf 3DENTIFICATION

8. MATERIAL PROPERTIES (HUBS C. MATERIAL PROPERTIES tRIMI

8. mulLDIhG BLOCm 60 1.

TYPE ,C, C. 18 SKIN. v.5. tuSI a gJq g 2. uNII SAN ONOFRf al 2. SUPPLIER: M WAL H[PP.J5 T ALL b[ C e

3. CusioMER:

50. CALIF. [0.

3. v.5.

(Mill

3. v.5.

EMSIs 4 LPs 1 9 U.T.S. 4W514

2. U.T.S.

INSIl 5. SOCAIIGN 6f N

5. ELONGATION

3. ELONGATION 6.

DISCS 6 6. R.A. 4, R.A. f 7. If51 ho. 1C82297 7. FATT GDfG.F8

5. FATI 40EG.Fs

8. R.I.

IMPACitFI.L8.8 6. R.I. IMPACTEFi.LB.3 9. U.S. IMPACT TEMP.

7. U.S.

IMPACI f(MP. tDEG.F3 IMPACI.Fi (DLG

10. u.5.

IMPACT [hG. S. U.S. [NG. (Fi.L8.3 (FI.L8.9 U.S. aIC

9. u.5. nIC taste 50RitIN.Bl (N5Ie5QRitIN.8)

D. C e<[ M I S T R Y C b MN b SI b P b CR b M0 L y E ~1,c,C C 'l ,C,( C 3 ,C,C C 3 ,c,C C 3,C,C E 3,C'C,E 3 (,,c e "I b.C. C. A5 b,c,C 58 b,C, t SN b, C,f. AL k,C, C. CU _ L,C, C,__ 5 L., C, E (. BORE STRESS F. CRACa OATA SPffD GRPM3 Siset si ( 3. tono insis

3. A-CR-OP 81800 RPM 3 (IN.3

2. 2305 412sta Emill

2. A-CR-05 40wtR5 PEE 0!_434.)

a.. Stesultf balA b

f q= 9 a 1. GPL88 l(NP. n[IAL ILMP,11UR (DLG.F8 2. Fu e im,ee e I a. s a al A /.l t 6 i s. / It t 9

s Tca.Qe t. ( Skee4 i3 4 24) Tusble Tsc A4-GD g Th ha. ( 44 10 e : 0060308603 LP IURBIN[ DISC thFORMATIch A. Uhlt IDtNIIFICA110N

8. MAffRIAL PROPERTI[5 GHUBD C. MATERIAL PROP [RIl[5 ERIMI

( 3'P C.f-g"c q 18

1. multDING BLOCS 80 1.

TVPC SM5183 (Mth. v.5.

2. ohlt Sah Oh0f RE st

2. SUPPLIER:

MIDW ALL HEPPl35f ALL. b.C.C _ _.(MSIS. _. 8

3. Cui10ME R:

50. CAtlf. [0.

3. v.5.

(MSIS ~ 3. Y.5. 4. LPs 2 4. u.1.5. taill

2. u.T.5.

En513 8 totall0N LOW

5. [LONGATIch

3. [LONGATION 9.

R.A t. DI5(s 1 6. R.A. F. IE SI NO. IC897*3 7. FATT e DE G.F 8

5. FAII 40EG.'FI'

8. R.I.

IMPACitF1.L8.3

6. R.T.

IMPACl4Fi.L8.3 9. u.5. IMPACI TEMP.

7. U.S.

IMPACI IfMP. 4DEG.F8 (DEG.F3

10. U.S.

IMPACT ENG.

8. U.S._IMPACI [NG.

4FI.L8.8 (FI.L8.9 II. U.S. KIC

9. U.S.

MIC (W5IoSQRitIN.8) .l (K11 50RitIN.33 D. CH[M15IRV MA b SI L P b CF E MO h W b C b C 3.C.C 0 3,c c E 1 c.c. C 7.C.C C 3 C.eC J.C.e E 7 .c. C i m A st 58 6 6 s u L 3..C.c Es 3 .e E 7 .c.e [5- ]t,s.c C.L ]u.c.e ((o 3.c.c..E 7 .c.e E. 60RE SIRE 55 F. CRACM DATA ~~' ~~- g c,g SPIED (RPM) SIR [55 h,c,e I. 1800 ansll

l. A-CR-OP 41800 RPMb (IN.9 2.

2305 817813 4a5IS

2. A-CR-05 40VERSP((08 1186 3.

6. StRtICL Dala b,C, e. r !. OPER. IEMP. METAL TEMP. qa infG_F1 2. t.almated mas dA/JT ( E st / it t p 3. Calualated man camck stre (In) 4. umalo of calculated su critical crack elze l 1 -..,. T

'To.ble I ( Sleaf 14 cf 24) t Tu<b h 'bkc h %. I W(. ls tute (tD{ T M 10 a z D080803603 LP TURBINC DISC lhf0RMAf!ON A. UNIl 10tNIItICAI!O4

8. MATERIAL PROPERTIES IHUB3 C. MATERIAL PROP [RTI(5 TRIM 3

3. bulLDIh4 BLoca 80 1.

IvPC b T8 3.C.C EMIN. v.5. tuSIBI ' ' () ~e, t

2. ukl1 Sa ss ONOF Rf al 2.

SUPPLI(R: M DWAL[ HEPP QSTALL. b.T.C,.. __ 8mSID__ I 3. CoilOntR:

50. CALIF. ED.

3. v.5. tuSIs v.5. 4 tPa 2 4 U.1.5. EmSI) . c.T.5. ENSIS

5. toCAIION Low

5. fLONGAIION

3. [LohGAI!ON t.

DISCa 2 6. R.A. 4 R.A. 7. Ifit WO. B073873

7. FATT tDEG.F3 6 F ATI.IDEG.F8 _

6. R.I.

IMPACitFT.LB.3 6. R.I. 'APACTEFT.LB.8 9. U.S. IMPACT TEMP.

7. U.S. IMPACI TEMP.

iMai!?i.. G.. ..o.5.xMAIS?44G. - iO. o.5. tri.L 8Fr.L II. U.S. EIC

9. U.S. MIC tuSI*SQRit]N.8) gM51*$QRitIN.ll D. CHfMISTAT c

SI s P s CR s Mo c 6 E 3v.< L 3..e c 3.e.e C 3 e.c C 3.c.e c 3.c.e. C 3 .e.e C M~ s .5 c

5. sy E > 3.u E 3., c E7 E

3.e.e E ] t. e.e E 3.c.e E_53.e.e 5-s AL Co t c

1. BORE STRE SS F.

CRACK DAIA SP((0 SRPM3 STRf55 _ ( 1800 4M5Il I. A-CR-OP 81800 RPMt TIN.3 2. 2305 812848 ta'18

2. A-CR-05 sow [R5P((08 IIw.) __

6. SERWICE DAIA ,.ee l. OP( R. I[MP. MEIAL I[MP. HUB (D[G.FB 2. Est imated man JA/JT (Ist/H r ) 3. Calculated mean ca.as k a.ize (Isa) 4 kat to of calculat.-J so critical crack of ze g L

,., < ~,.. ui.b i (sLod er of 20 rA w h WesG@c herid. g 10 m : 00s0101603 LP TURBINE OIic IhFORMA110h A. Ubit IDi4IIFICAIION

8. MAlfRIAL PROPERT;[5 GHUB3 C. mal [ RIAL PR OPE R I l[ 5 (RIM 3

3. bu!LDING SLOCm 80 1.

TVP[ .. 3 >,C. C 18 (Min. v.s. tustie i -,.e e Dw A LE ME PP [.7sil ALL,,, b,c,g 2. unti SAN ONOT H[ st

2. SUPPLIER:

M a I ~ 3. v.5. (Mill 3. Cui10Miez

50. CALIF. [0.

3. v.s. tasta 4.

LPs 2 4 U.T.5. (mill 2. U.T.S. tuSIS

5. totAIIOm 60w 5.

[LonGATION

3. ELohGATION t.

DIsra 3

6. D.A.

4 R.a. 7. Ifil h0. IC73876 7. FAII 80fG.F3 S. FATI EDfG.Fl 8. R.I. IMPACitFT.LB.3 6. R.T. IMPACTEFT.tB.8 9. U.S. IMPACI 1[MP.

7. U.S.

IMPACI T[MP. 8 0E G.F 8 40EG.Fa 10. U.S. IMPACI (hG. 4.. U.S.__ IMPACT [4G. (F3.LB.8 (FI.L9.3 31. U.S. MIC

9. U.S. MIC 4N5I*50RTeIN.88 J

tn52 50RT4Ih.33 D. CHEMISIWY C b M 8s b SI b P b CR b ft 0 E 3 .C.C C 3.C.C C 7 C.C E 3,c.C C 3.C.C E 7(q g E 3 c g g b 1,c.P .t c.c. e CU s.c. c _ s s.c. e u.c.e A5 b.e, C s8 c.C, c s-I E. BORE SIHEis F. CRACM DATA. SP((D (RPM 3 STRESS ( 3. 3800 inill I. A-CR-0P (1800 RPMB (IN.3

2. 2305 412843 imill

2. A-CR-05 (0WERSPEED) liss,)

.'3 G. StkwlCE DATA b.c. e_ 1

n. oct u. If MP. M[lAL IEMP. itMS,jQ{G [B, g

2. t' tamateJ man JA/JT ( l a / lir ) 3. Celsulated man crack mtze (In) 4. kativ uf calculat=J to critical crack size I

1 T o.ble 1 ( 6L2ct 16 of 24) Tw Wie. %c %.k. Wes%)bou brh ID a z 0080301603 LP TURBINE 015C INFORMATION A. ohls IDENIIf! CATION B. MalfRIAL PROPERTIES (HuS3 C. MATERIAL PROPERIIES GRIMI I. euttGIAG BLOCm 80 1. IvPt ,w.C.C-TB (MIN. v.5. 'j tusils b*q* g WALL H[PPFNSTALL b,C.8 2. uhBI SAM Oh0FRf el 2. SUPPLIER: M 3. Cusiont N:

50. CALIF. [0.

3. v.5. tusis Y.5._(MSIl_ _ _. 7 4 (Ps 2 4 U.i.5. INSII . U.i.5. inill

5. LOCATION Gov

5. (LONGAI!ON

3. [LONGATION

( 6. DISCa 4 6. R.A. 4 R. 7. I(si 40. 1073881

7. FATI 4DfG.FB 5.

FA I _ ( D E G'.8" )__ I 8. R.I. IMPACitFT.LB.4 6. R.I. IMPACTIFT.LB.3 9. U.-5. IMPACT TEMP.

7. U.S.

IMPACI T(MP. (DE G.F 3 (D[Q.f3

10. U.S.

IMPACT ENG. . 4..U.S... _IMPACI ENG..._ tFi.LB.3 (FT.L8.3 II. U.S. mIC

9. U.S.

MIC tuil*50RitIN.88 I sL119 50 R i lI N. 9 ) L. D. CHEMISTRv 0 6 6 SI u P 6 cR u 6 v b E 3.e.e LM 3.c.e L a.c.e E 3.c.e E J.c.e Cno 1.e.e_T _. 1.c.e s A5 s 58 6 SN s Cu s c E 3.c.c E 3.c.c E 3.e.e E 7,c.c [at ]6.c.e E 7.c.e.T>- 3 'c'e E. BORE SIRf55 F. CRACK OATA ' - - ' ~~ ~ SP((0 4 RPM 3 51R[55 ~ 1. 1800 48518

1. A-CR-OP (1800 RPMB (IN.9 2.

2305 412ata (M533 2. A-CR-05 (OWfRSP((D)_,({N.),_,,, b. StRulCf DAIA g D.C.C.

1. opt e.

ILMP, MLIAL I(MP., HUB 40EG.F8 2. Ent smated mas dA/dT (lu/Hr) 3. Calculated mas crack size (In) 4. katso et calculated to critical crack aire l' ~ ..we-..

Tekla 1 ( Slaci r7 4 24) Tutkic lisc Ab l 3 e.u %.griebg b Wesf 30 m b08 0 8 0 8,0 5 I LP TuRBIk[ 015C thf0RMATION

a. Uhlt IDthTIf!CATIch B. MalfRIAL PROP [Ril[5 (HUBS C. Mk;)(RIAL PROP [Ril[5 tRIN3 iMIh.

V.S. L-l,.C.C-g q* q t 18 1

8. edILDIhG BLOCm 80 8.

Ivet tasill s 2. unti Sah ONOIk[ st

2. SUPPLICR; MIDW A L E NE PP,Lis5 T ALL.,6,C,C

..tuSIl._. 9 3. Cu5 t ont h:

50. CALIF. [D.

3. T.5. tuSIs

1. Y.5.

4 LPs 2 4 u.1.5. Insil

2. U.T.S.

(MSIS

5. LOCATION LOW

5. [LohGATION

3. [LohGATION E. DIsta 5

6. R.A. 4. R.A. T. Ifii h0. 1C13e92 7. Fait 8DEG.Fs

5. FATI 4 0E G.F 3

8. R.T.

IMPACitFT.L8.8 6. R.I. IMPACitFT.L8.3 9. U.S. IMPACT IEMP.

7. U.S.

IMPACT TEMP. 40CG.F8 (DLG.F3

10. U.S.

IMPACT [NG. 8...U.S.~ IMPACT LNG. (Fi.L8.5 (F1.LB.3

11. U.S. mIC

9. U.S. mIC (K5I*50RitIN.88 L

_L - IKil*50RitIN.8) D. CufMISTRY C b Mk b 51 5 P h h MO b W b E 3.c.e. E 3,c,c. C 3.cc C 3,C,e [ CR 3,c.e C 1 ,C, t* C 3,C,R Ewr 3,c,e E 3,c e [ 58 ] b,C,c [ 5= ]6,cc[At ] b.C,c [cu ]L,,c,e C 3 (,,c e 6 A5 6 5 E. BORK SIR [55 F. CRACa DATA - - ' ~ ~ - h y,g~ SP[ED eRPM3 STRE55 h,c,e 3. 1800 in5It

1. A-CR-OP (1800 RPMB (IN.3

2. 8-CR-05 60VERSPEEDI IIN.)

2. 2305 482848 (mill

.] h. $[Rv!CE Data b.C C 1. OPER. 1[MP. MEIAL ILMP H g_4 DIG.F 3 2. Estimated man dA/JT (lanfHr 3. calcialated man crack size (In) 4. kat to of calculated to critical crael. alas d

t T d le 1 ( Sleet it 4 24) 4 Lc. Disc. hk Wes+%bose Proc cMq ID e : D08030I603 LP fur 8INE DISC INFORMATIOh (hub) C C. MATERIAL PROPERTIES (RIMI 8. 0411 10thBIFICAi!04

8. MATIRIAL PROPERTI[5 97 18 1.

es ul t is t h6 B L O C si 40 1. ITPE GMIN. v.s. ( 3 tuSIll [ 2. u%II SAh 040FRE st

2. SUPPLIER:

MTo v a L L HE P PJ.35 f A L L, h/,8, v.5.__.tuSIs .**t

3. Cuis OMt R:

50. CALIF. EO.

3. v s. tails 3.

o. L Ps 2

4 u.I.S. tusil

2. U.f.5.

in513

5. totAi!ON GOW 5.

[LONGATION

3. [LONGATION 4.

DISCS 6. R.A. 4, R.A 7. If5T 40. IC82296

7. FATI EDEG.F3

5. FATI GDEG.r F 8.

R.I. IMPACitFT.tB.3 6. R.T. IMPAC14Fi.tB.3 9. U.S. IMPAC TEMP.

7. U.S.

IMPACT TEMP. '4.U.~5.7Mhh'hNG. ~'

30. U.S.

IMP 'E G. EFi.L8.8 GFI.L8.3 II. U.S. mIC

9. U.S.

KIC EM5I*$0RitIN.83 (E5I*50RitIN.sl

o. CMcMIstRv C

b Mk L 6 be M0 L E 3,c,e C 3,c.e [SI 3 ,c.e (e 3 ,e ( CR )b.c.c C '3 SE C.V-)b,e.e s SN s AL s cU b 3 h L 3.c.c. C5 ]s.c.e [ 58 ]s.c.c C 3.c.e C 3.e.e E..'l,c.c.E. 3.c.e _ E. symt S t at S5 F. CRACM DATA - - ~ {g - - -- - --- SPEED GRPMI SIR [55 _gg 1. 3a00 (MSIS

1. A-CR-OP (1800 RPMB (IN.)

2. 2305 412813 tuSI8

2. A-CR-05 ( 0 W E R SP((() D, t I N. ) __

j. l L. 5(RwICE Data b.C e t \\-~ 1. O Pi k. I(MP. MLTAL I{NP, HU8 (O[6.F 3 2. EatinateJ anas dA/JT ( I a / te r ) 3. CalculateJ mas crack size (In) 4. Rattu of calculated to critical csack afze L G me.-. 2 ) l

Takb i ( 5keci 19 d z4) Tu< bke bac h WeSM buse P8ofrie+*g 3 I lb a : 06a010160= LP fur 8Inf DISC IhFORMATION A. Uhtt IDthlIFICATION

8. MAffRIAL PROPERTIf5 4HUSS C. MalfRIAL PROPERTIf5 4RIMI

1. mult0thG BLOCm 80 8.

TYPE {90.O]s.C.E 18 (MIN. v.5. (K5133 4

2. Uhli 5AN ONOFNE el 2.

SUPPLIER ',, ~ ,,,, I,(C ( J ,*e*p

3. CuS10nf R:

50. CALIF. [0.

3. V.S. ENSIl 1. Y.5 ENSI)

e. LPs 2

4 U.T.5. ta5Il

2. u.T.5.

ausI)

5. LOCATION GE h

5. fLONGAIION

3. f LONGA TION

6. 015Ce 1

6. R.A. 9. R.A 7. If51 40. ICa229s

7. FATI 40[G.FB

5. F A T I 4 0 f G.'F 's

8. R.I. IMPACitFT.LB.3 6. R.I. IMPACitFT.LB.3 9. U.S. IMPACT TEMP. 7. U.S. IMPACT TEMP. 4 Of G.F k 4DEG.f3

10. U.S.

IPPACI thG. __. a. U.S._. IMPACI thG. EFI.L8.8 EFI.LB.3 II. u.5. aIC

9. u.5. KIC (MSI*1QRIflN.33

._._ su11,50R* TIN.33 O. CH1MISIRV C 6 M t. SI s e 9 CR s n0 6 C 3.e.e c

1. c.e c 3.c.e c 3

.c.c E 3.e,<.t 3.c.e. L. ]e,e.e. s 5 6 5 6 g i.p.< g.5 3.c.c g.3..e g 3.c.c C i ' ' E '" Y ' '* - d P ' * ' ~

t. 800f 5tuf 55 F.

CRACm DATA SPffD (RPMs STRE55

s. sono imSIS j

A-CR-OP (1800 RPMB (14.3

2. 2305 attat:

Eastl r A-CR-05 40ptR5PI[DI_1181 1.__._ G. ituellt GATA ~ - b,c, e

1. OPtk. }fMP. METAL ](MP, HUB GD[6.F3 2.

Eatiaated m.sa JA/J1 ( l as / llr ) 3. Calculated mas crack size (In) 4. Ratio of calculateJ to critical crack size L a. e e es eme e6e me 6m-

T4.le le 1 ( 6keei ao d 24) Turkhe luc hk. LAes E ) k m e A grie4ug i o., im. o i o i t.o-LP TUR8Ih[ 015C INFORMATIOh A. uwit IDfklIFICAIION

0. MAIERIAL PROPERTI[$ EH 88 C. MAT [ RIAL PROPCRII[5 ERIMI 3.

SulLO!hG 6LOCu 80 1. TYP[ .NE 18 -g eMIN. v.i. EN5188 Dv Atk 01[PP(N514LL., b C.C ..v.5.._(Mill _. _ F i f t. e 2. Uhlt 5A4 ONOFe[ st

2. SUPPL IER :

M

3. CuSIO9tR:

50. CALIF. [D.

3. v.5. EmSII 4. LPs 2-4. u.T.S. ed5Il U.1.5. SuSI3

5. LOCAIION 6t h

5. ELOh6ATION

3. [LONGATION 4.

Olife 2 6. R.A. 4 R.A. T. T[5I 40. 1082295 T. FATT EDIG.F3

5. FATI (O[G.ft 8.

R.I. IMPACTEFi.LB.3 6. R.I. IMPACitFI.t8.8

9. U.S.

IMPACI TEMP. T. U.S. IMPACT TEMP. tDEG.F8 IDEG.fi

30. U.S.

IMPACI ENG.

8. U.S._.IMPACI (NG.

4FT.LB.3 (FT.L8.3 !!. U.S. EIC

9. U.S. MIC EM5I*50RitIN.88 b

in51*10RitIh.33 D. CHEMI5IRT C M 6 5 6 s CR c 6 c c 3 e.e E 3,c.e E, 3.c.e E. 3 e.e C .1.c. e C 3.<. e _ C,_. 3 .c. e g i g.< g p.e.e g Se f..< g p.e.e g p.e.e.C'"TE3 A5 5 At t. soRf stat 55

f. CRACK 9ATA SPEED GRPM3 STRfis 8,c,g, g,

3 I. 1800 EmSIS

3. A-CR-OP (1800 RPMS (IN.8

2. 2305 812848 Skill

2. A-CR-05 (OWERSPEEDI ( { N. )_

G. SERWICL DAIA - 1,c,c, 3. OPER. I[MP. MEEAL I(MP. Em e nr G,{,) 2. Estimated aan dA/JF (In /ttr ) 3. Calculated man cea.k alze (la) 4. katio of calculat=J to critical crack afze L. s I

~Ta.bia 1 ( Skeeia. d 24) I ur his< 'b&c %% ta,a,56" brd-% ID e : 0080808609 LP TUR8th[ OISC INFORMATIOb A. ukII IDthBIFICAIION

8. MATERIAL PROPERTIES (HUB 3 C. MAI(RIAL PROPERIIt$ TRIM 3

l. 5,C.C 18

3. DUIL DING BLOCK 80 1.

TVPE 4

• e
• e, enste inIn. v.s.

2. uMIT SAN ONOFRL st

2. SUPPLI[R:

M DWALL HE PPI)1I ALL,, h'(** d

3. (usiontas so. CALIF. (D.

3. v.5. an5ft 1. v.5. 4MSIS 4 LPs 2 4. u.T.S. imSIB

2. U.1.5.

ENSIR S. LOCATION GI N S. flohGA110h

3. E LONGAi!ON 4

DISCS 3 6. R.A. 9. R.A. F. I( S i No. 1C73662

7. FATI IDE G.F 3

5. FATI (DEG.Fl 8.

R.I. IPPACiaFT.L8.5

6. R.T.

IMPACitFT,L8.1 9. U.S. IMPACI TE MP.

7. U.S.

IMPACI TEMP. (DEG.Fa (DEG.Fa

80. U.S.

IMPACI ENG. 8._U.S.._. IMPACI ENG. 4FI.LB.3 (FT.L8.3 II. U.S. mIC

9. U.S.

mICtKileiORitIN.it (K51*1QRitIN.Il _i D. CHEMI5 thy C 4 6 51 b P k CR b b E 1.c,td L MN 3 .c,( E 3 .C,e C 3 .C.C E 3 .C.C C"0 3 8.C.C C '. 3 ,f,R 2 2 a C 3.e,c C 3 ,c E ~1 .e.c [5= ]6.c.c[AL ]6.c, e [ as _]L.c.e-. E 3 s, e, e 1 s As L< s8 6 a [. Is0wt SINE 55 F. CRACA DATA _ b,C, C hPLCD GReps STR155 ( 3. 8800 ansil

1. A-CR-OP (1800 RPMB (IN.8 2.

2305 (12843 tm113

2. A-CR-05 80VERSPEED).1Ih.I

'_1 G. StevlCE DAIA - b.C,c l. OPEW. ILnP. MLi&L I[MP. una EDf, M 8 2. Estimates ada JA/JT ( I n /lig ) 3. Calculat=J aan crack size (la) 4. katto of calculated to critical crack alze

( Slec4 as cf 24 ~ ' Tit.la t l m We. %c h+ tapFja S th Mt ID e e 00a0101a.0= LP TURBINE DISC INFORMATI0h A. UhlB 10thtIFICATID4

8. MATERIAL PROPFRTICS EMUSB C. MAT [ RIAL PROPERIIES tRIMI

1. bultolhG BLets 80 3.

TvPi ,C. C T8 HEPPQSIALL'h,C,C h.c.g (MIN. V.S. tm5188 2. use I I SAh 040 rut al

2. SUPPLIfR:

M WAL 3. CUSTOMER:

50. CALIF. [0.

3. Y.5. taste l l. v.5. (MSII 4 tem 2

e. u.T.5.

Em518

2. U.T.S.

En513 S. L OC AIION GE N

5. ILONGATIOh

3. fLONGATION L.

DIsta 4 6. R.A. 4, R.A. 7. TE ST hc. IC73sT7

7. FATT 80CG.Fs

~'5. FAff~tDEG.F8 s. R.T. IMPACitFI.LB.5 6. R.T. IMPACitFI.LB.B 9. U.S. IMPACT T[MP.

7. U.S.

IMPACT IfMP. 801G.F3 IDEG.f 3

30. U.S.

IMPACT (hG. " 8.~U.S.~1MPACI thG. ~~ (FI.LB.3 (FI.LB.3 II. U.S. mIC 9. U.S. MIC (K5Ie50RitIN.83 J .gn5Ie50RitIN.33 L D. Ceef MI SIN T s M s Si s s CR L M O. s s C.C A.c.e C.3.c.c C:3.c.e L~e _3.e.e C 3.e.e E 3.c e_Ev 3. c. e s s 5. t a s CU s 5 c E i.3.e.e EA 5 ~1...e E 3,.c.e [ 5- ] s,c.c E 3,se_E ._J,c.e_E 3, c. e 1. B0kt SINE 55 F. CRACM OATA - ~~ ^ ] g ~ SPEED ERPM3 SIR (55 1. 1800 Em513

1. A-CR-OP (1800 RPMS (IN.9

2. 2305 612sta im519

2. A-CR-05 10VERSP[ G3 (jm,)

6. SEsewICE DAIA ] b C.O 9-*

1. opt R.

ILMP, M[IAL T E nP. tIUB EDFG [J__. 2. Estimated man dA/JT (lu /ft r ) 3. Calculated mau canck size (In) 4. hrso of calculated to critical crack size j

l idle i (six4 2a.4 24) i Tom wo u U.5-h k a % pie 3D e z D69080860* LP fur 8INE DISC INFORMATI0h A. ukl3 IDftflFICalION (RIAL PROPERil[5 EHU68 C. MATERIAL PROPERVIES TRIM 3 ]g,c,f T8

1. bulLDIhG 8t0Cm 80 IvPf anIN.

v.5. [ tusts3 ~ $*q*t 2. UNIT Sah ON0FRF m3 . SUPPL 1[R: MTDvaLL HEPPf lp5I AL L - 3.C,C {

3. CuilonfR:

50. CALIF. 10.

e. v.5. tasta l' 3. v.5. EusIn 4 LPs 2 4 U.I.S. Emi!I

2. U.T.S.

ENSID 5. Localloh 6t h

5. [LONGal!ON

3. (LONGATION 6.

D15Ce 5 6. R.A. 4. R.A. 3 If 51 NO. 1L7386=

1. FATI (Df6.F3 5.

FAli (DfG.F3 6. R.I. IMPACT 4F1.LB.3 6. R.I. IMPACitFT.LB.3

9. U.S.

IMPACT TEMP.

7. U.S.

IMPACI TEMP. EDLG.F3 40EG.F3 .... _ _ _IMPACI thG.

10. U.S.

IMPACI th6. S. U.S. 4FT.L8.3 EF1.LB.3 II. U.S. mIC

9. U.S.

MIC tast*50RitIN.33 istSIos0Ri t j n. 3 3 D. (est nI5 f p v I b b C f_ P b CR b b m b LC 3>,C, et C 3 c,C [SI 3 E 3 ,C,C C ~1 ,C,t* Ett0 ~3,C,6T ~1 ,C, t"_ Mh s L t - At L cv 6 5 6 3,c c [ A5 ] s,C, e [ 583 .e,e ( 5= 3 .c.e 3,c.e E .3,e.cE 3 ,c, e L t. Bout SIRI 5 5 F CRACm DATA SPEED 4RPMg Sikl55 3. 1500 im5il

1. A-CR-OP (1800 RPM 3 (IN.3

2. 2505 412888 Em518

2. A-CR-05 40W[R$PELO3 ilN.1 G.

SERwICE DATA - 6.e.e - - - - - ~

1. OPER. I(MP. M[ T A L ]E ftPut1111 ADLI U-._.

l 2. Estimated man dA/dT (In/Hr) 3. Calcanisted mas crack size (In) ~~ 4. Ratio of calceslated to crl:1 cal crack size j L 3 s

taw t ( Skeei 24 4:4 24) .1 Tu4 h %c hb.

• Paa r %

a %F 3%e IC a. 00803086C= LP fuRBIN( DISC thf00 MAT 10W A. UkII 10(nflFICsIl0%

8. MAT [ RIAL PROPERi!E5 (MV83 C. MAffRIAL PROP (riles ERIM3

1. BUILDIIe6 BLOCm to 1.

TVPE . J.f. t' 18 EMIN. Y.5. tailDS 3de 2. uhls '3Ah 040f ME st 2. SUPPLifR: M WAL et[PP(451ALL % h,(,(l. f 7 a

3. CUSIOutR

50. CALIF. [0.

3. Y.5. imill V.S. ENSIS 4 LPs 2 4. U.I.5. taill

2. U.I.5.

Emi!I S. totaIION GE h

5. ELONGATIch

3. ELONGAI!ON L.

DISCn L 6. R.A. R.A I. T( 51 NO. 1(evi=2 I. FATI 4DfG.F3

5. FATI 40tG.F3

8. R.T.

IMPAcitF1.L8.8

6. R.I.

IMPACitFI.LB.3 2 9. U.S. IMPACT TEMP. I. U.S. IMPACI IEMP. IMPACT F3 40[6 E DE 6.F e 10. U.S. IMPACI [NG.

8. U.S.

EhG. EFI.L8.9 (F1.L8.3 II. U.S. MIC

9. U.S.

NIC 4K51850RTIIN.65 E N SI*SQR T 4 los. s ! L. (ntalsIWV r. te si (4c,e P h CR _I NO s 3 e L h i. 1 .C, t* L_ M k 3(c,e c i3 C 3,cA C .\\,c,e C ,3 ,c,t>,E 3, c, e. 8 A5 18 b 5 b At b tu sg t L_ al 3,.cA C 3(g L 3,c.c L " 7 .t.C E 3,c, e E 7 ,e _ E > 3,, c, g>

4. 60pt 5thtS5 F. CRACE DATA

' - - ~ ~ ~~ b,c,C ~~ SPE E D ERPMB STRESS 8. 1800 Emill l

1. A-CR-OP 81800 RPn3 IIN.3

2. 2I05 el2sts Ems!I

2. A-CR-05 t ow[R5 PEE D S _!)es. )

6. StevlCE DATA g 1. Opt R. ItMe. MtIAL It pf. MVB 80[6.F I 2. Estimated man eta /JT ( I n / ts r ) 3. Calculated mas crack sizer (In) 4. katio of calculated to critical crack stae l i

A Blade / Bucket No. Ae Be D 59T 9" 3/8" 1/8" B 62L 12" 3/8" 1/8" 71T 10" 3/8" 1/8" 74L 12 1/2" 3/8" 1/8" u 103T 9" 3/8" 1/8" 106L 10 1/2" 3/8" 1/8" A = 8" 8 = 1/2" l A - Erosion Shield Width 8 - Erosion Shlstd Length Stage L / Ae - Erosion Width / Turbine LPB Be - Erosion Length D - Erosion Depth Date 9/24/78 ,~ L - Leading Report No. OCl-3 T - Trailing Page 1 of 1 n!RBINE END EltOSICN/ DEFECT LOCATION OtART

e . 4 n A Blade / J Bucket No. Ae Be D l 103L' 11" 3/8" 1/8" 8 106T 3/8" 1/8" l 123T 10 1/2" 3/8" 1/J" I i 126L 11 1/2" 3/8" 1/8" y 147T 10 1/2" 3/8" 1/8" 150L 11 1/2" 3/8" 1/8" A = 7" 8 = 1/2" I i 1 i l A - Erosion Shield Width 8 - Erosion Shield Length sg,g, g / Ae - Erosion Width Turbine LPS Se - Erosion Length D - Erosion Depth Date 9/24/78 L - Leading Report No. S01-7 T - Trailing Page 1 of I GENERATOR END EROSION / DEFECT 14 CATION CHART

/J A' Blade / Bucket No. Ae Be D l 17T 10" 3/8" 1/8" 8 ^ 20L 11" 3/8" 1/8" 1737 9" 3/ 8" 1/8" i 176L 10 1/2" 3/8" 1/8" o 193T 9 1/2" 3/8" 1/8" 196L 10" 3/8" 1/8" ) ) A= 7. 75" ' B= .50" l 't l I A - Erosion Shield Width 5 - Erosion Shield Length Stage L Ae. Erosion Width T@e LPA 7 Be - Erosion Length [- D - Erosion Depth Date 9/24/78 L - Leading T' T - Trailing ) Report No. OCl-1 3 // Page 1 of 1 TURBINE END EROSION / DEFECT thCATION OMRT r

e*.4 j J R: port No. Date 9/24/78 Stage L Turbine LPA, LPB l i t b 4 BIADE 1 3 V I b L / Y ROTOR DISC {] l h I l l l I I STEEPLE /GRISTMAS TREE AREA TYPICAL EROSICN LPA 4 LPS TURBINE AND GENERAMR END ., -. J}}