Text

Reactor Bldg Cool Air Supply Ducts,Testing & Evaluation
	ML19326B510
Person / Time
Site:	Arkansas Nuclear
Issue date:	03/31/1974
From:	; BECHTEL GROUP, INC.
To:	;
References
	NUDOCS 8004160306
	Download: ML19326B510 (123)
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RDBM Gia REACTOR BUILDING COOL AIR SUPPLY DUCTS

. TESTING AND EVALUATION s

tn JOB NO. 6600 ARKANSAS POWER AND LIGHT COMPANY U$y ARKANSAS NUCLEAR ONE H

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BECHTEL POWER CORPORATION P. O. BOX 3965 SAN FRANCISCO, CALIFORNIA 94119 N

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0 TABLE OF CONTENTS Page 1.0 Introduction 1

2.0 Analysis of Safety Implications 2

3.0 Duct Design Loads 2

f 4.0 Duct Test Description 3

i 5.0 Duct Test Results 5

I 6.0 Conclusions 9

O 7.0 Corrective Action 10 Appendices A.

Report on Duct Test No. 1 Report on Duct Test No. 2 B.

Survey of "As-Built" Welds for Cool Air Supply Ducts C.

Seismic Analysis of Typical Supply Duct 1

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LIST OF TABLES Table Title I

Duct Design Requirements and Test Results P*

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T4' LIST OF FIGURES Figure Title 1

Reactor Building Cool Air Supply Ducting Plan Below El. 357'-0" 2

Reactor Building Cool Air Supply Ducting Plan El 357'-0" to El. 376'-6" 3

Reactor Building Cool Air Supply Ducting Plan El. 376'-6" to El. 401'-6" 4

Reactor Building Cool Air Supply Ducting Plan El. 401'-6" to El. 424'-6"

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5 Reactor Building Cool Air Supply Ducting Section AA 6

Reactor Building Coo) Air Supply Ducting Section PB i

7 Reactor Building Cool Air Supply Ducting Duct A 8

Reactor Building Cool Air Supply Ducting Duct B 9

Reactor Building Cool Air Supply Ducting Ducts D and E l

10 Reactor Building Cool Air Supply Ducting Ducts C, F, G, and H 11 (D

Reactor Building Cool Air Supply Ducting Duct Plenum J

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.l. 0 Introduction-A review of the Reactor Building ductwork revealed that the de-sign of the cool air supply ducts and plenum may not completely conform to the requirements stated in our design specifications.

The cool air system is shown in Figures 1 through 6.

The design specifications require that the ductwork be able to withstand the combined effects of seismic loading and the differential pressures resulting from rapid pressure buildup during a loss of coolant accident.

An analytical approach was first used to analyze the ductwork under the above loading conditions.

It was determined from this analysis that the effect of seismic loading on the structural capacity of the ducts was minimal, and that the differential pressure loading was the governing loading condition.

It was further concluded that the present relief valve arrangement and relieving characteristics of these valves do not assure a proper-ly low pressure differential compatible to the structural inte-grity of some sections of the supply duct system.

Because of the complex and redundant nature of duct behavior under the differential pressure loading condition, pressure tests were conducted on representative full scale duct s ecimens in i

order to evaluate the validity of the analytical approach.

The results of these tests showed that the methods used in the analytical approach were conservative.

Therefore, it was decided to develop an acceptance criteria for evaluating the structural adequacy of the duct system based primarily on test results.

Furthermore, a comprehensive field survey was performed to define the "as-built" conditions of the cool air supply ducting.

This

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survey included locations and arrangement of duct stiffeners, I

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hangers, transitions, bends, and stiffener and hanger welding.

The main purpose of this survey was to note any deviations bet-ween the "as-built" conditions of the ducting and the correspond-ing duct test specimens in order to determine the proper correct-ive action required.

Although the ducting was generally found to have a sufficient margin of safety against failure, some areas will require modifications to completely satisfy design requirements.

The extent of the corrective action required.is detailed under section 7.0.

2.0 Analysis of the Safety Implications The deficiency described above may result in collapsing portions of the ducts during a loss of coolant accident.

Damage to the ducts does not necessarily mean that a complete break-down in the operation of Engineered Safeguard R.B. ' Cooling System will The system may continue to operate through the distorted occur.

ducts.

However, efficiency of the system would be effected due to the decreased air supply.

The coollng capacity of the system would be below the values given in FCAR.

3.0 Duct Design Loads 3.1 ' Differential Pressure Loads The Reactor Building cool air supply ducts are-equipped with nuclear pressure relief var as manufactured by American Air Filter Company.

These four-part gravity valves are designed to open under containment pressure following a loss of coolant accident.

The maximum pressure differential from outside to inside of the ducts following a loss of coolant accident was deter-mined using American Air Filter Topical Report No.

TR-7101.

The equivalent round diameter and valve

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spacing was first determined for each installed supply 3

duct segment.

These values were then used in Figure 7.16 of the above Topical Report to obtain the maximum pressure differential in pounds per square inch fbr l

each duct size.

The pressure differentials were based l

on u 15 psi /sec. pressure rise which represents the i

j maximum rate of pressure rise during a loss of coolant accident.

This information is given in Table I, on I

page 12 3.2 Seismic Loads Seismic loads are taken from the Bechtel Power Corpo-1 ration Specification 6600-C-101, titled, "Specifica-tion for Earthquake Resistance Design of Equipment Located in the Reactor Building for Arkansas Power and Light Company, Arkansas Nuclear One".

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4.0 Duct Test Description 4.1 Two separate pressure tests were conducted to. evaluate the behavior and structural adequacy of representative 4

full-scale duct specimens under negative (vacuum) pressure loading.

Both tests were conducted by Barrow-Agee Laboratories, Little Rock, Arkansas, which is an independent laboratory.

The tests were performed at the shops of McCroskey Sheet Metal, Inc., Little Rock, who were the fabricators of the test ducts as well as

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the supply duct system for the Arkansas Unit One Plant.

The test specimens were fabricated to represent as.

I nearly as possible the existing supply duct system for the particular size of duct tested.

The following duct materials were used in both the test specimens and t.he existing ductwork.

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Duct Stiffener ASTM A-36 b.

Duct Panel 14 gauge ASTM A-525 galvanized sheet 4.2 Test No. 1 was performed on January 17, 1974 and involved pressure testing a 60" X 40" X 10' - 0" long duct specimen with 2d X 2" X 1/4 " angle stiffeners at 24 inch centers.

The duct was tested to a negative pressure of 2.86 psi and the test concluded before duce collapse or permanent deformation occurred.

Be-cause of the high pressure attained during this test, it was concluded that further testing was warranted.

4.3 Test No. II was conducted during the week of Feb-ruary 18, 1974.

The test program consisted of testing to destruction three rectangular and one round duct

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under negative pressure.

All ducts, e.xcept the round duct, were instrumented to measure strains'and deflec-tions at selected points on stiffeners and sheet.

Test Specimen No. 1 was a 20" X 16" duct with 1" X 1" X 1/8" angle stiffeners at 48" centers.

Test Specimen No. 2 was a 35".X 30" duct with 1-1/4" X 1-1/4" X 1/8" angle stiffeners at 32 inch centers.

Test Specimen No. 3 was a 35" X 30" duct with 1-1/4" X l-1/4" X 1/8" angle stiffeners at 16" centers.

The round duct speci-men was 32 inches diameter and 12 feet long with no intermediate stiffeners.

All rectangular ducts had a l

90 degree elbow.

Test Specimens No. 1, 2, and the round duct represented existing ducts in the Reactor Building air supply system.

Test Specimen No. 3 repre-sented additional stiffening on the existing duct, l

represented by. test Specimen No. 2.

A detailed des-cription of test specimens, procedures and desci ption

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of test data are included in Appendix A.

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4.4 A third test will be conducted to evaluate the ad'equa-cy of that portion of the supply duct system consist-ing of the 30" X 30" and 30" X 23" ducts.

The duct specimen tested will be representative of the existing 30" x 30" duct, which is the more critical of the two duct sizes noted above.

Upon completion of the test and evaluation of the results, an addendum to this report will be submitted outlining the results of our evaluation and stating corrective action if required.

5.0 Duct Test Results In addition to recording of strain gauge and deflection data, visual observation was made of the duct behavior during the course of the test.

In test No. II, 8 mm movie film was also made during both the testing and failure stages of the duct spe-cimens.

5.1 Test No. I 5.1.1 Duct Specimen:

6 0 " X 4 0 " duct, stiffeners at 24" spacing.

The duct was pressurized in appro-ximately equal increments to a negative pressure of 2.86 psi.

The test was concluded before collapse of the duct occurred.

A visual inspec-tion made after the. test indicated no evidence of inelastic deformations of the sheet or stif-feners.

5.2 Test No. II 5.2.1 Test Spechmen No. 1:

2 0 " X 16 " duct, stiffeners at 48" spacing.

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F A

B C

D E

PLAN The specimen was pressurized in 1/4 psi incre-ments to 3-1/2 psi and 1/2 psi increments there-after to duct failure.

During early pressuri-zation, snapping and popping of the duct was neard as the duct skin assumed an inward de-flected shape.

At pressures up to 3-1/2 psi Dd the tops of the duct were bowed inward and the sides of the ducts had a slight outward curva-ture.

At 3-1/2 psi, the dial gages were removed to prevent damage from failure which was thought to be ns

.r.

At 4 psi and above, all sides of the ducts were bowed inward.

At approximately 4-1/2 psi the welds at the corners of the stif-i fener frames began to come apart.

At 5-1/2 psi stiffener C bu'ckled across the bottom of the duct, and the pressure dropped.

About 5 seconds I

later, stiffener B buckled across the top of the duct and failed at center of span and simul-taneously there was a secondary failure of one lower corners of duct between stiffeners B and C, which developed a buckle.

Before these stiffeners buckled, the welds at the corners of the stiffener frames had almost completely.

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opened up.

The duct still held pressure after the buckling of stiffener B, but it was bent grossly out of shape and failure was assumed.

The first failure of stiffener was at 5.42 psi.

5.2.2 Test Specimen No. 2:

35" X 30" duct, stiffeners at 32" spacing A

B C

D d

E F

E PLAN f

F

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After observation of the failure mode of test Specimen No. 1, it was decided to add a strain gage on the outstanding leg of stiffener C.

The centerline of the gage was, located 1/4" from the top of the angle.

The duct was pres-surized in 1/4 psi increments.

At 3/4 psi a small bend appeared in the top leg of stiffener B.

It appeared as if this stiffener were start-ing to buckle, but when pressurization was con-tinued, no further buckling occurred.

At 1-1/4 4

psi, the welds at the corners of stiffener frame C began to crack.

At 2 psi, a noticeable twisting of the stiffener angles was observed.

At 2.82 psi, stiffener C buckled followed in quick succession by stiffeners D and then B.*

Secondery failure of upper duct corner between C and D developed 7.nd a leak developed in the duct.

)

5.2.3 Test Specimen No. 3:

35" X 30" duct, stif,-

feners at 16" spacing A

B, C

D E

F G

n E

o H

I J

PLAN Duct was pressurized in 1/4 psi increments.

At 2-1/4 psi, there was a noticeable twisting and bow in stiffeners G and H along the top.

At 3 psi, there was a slight bow in stiffeners

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B, C, D, E, and F and about a 3/8" bow in stif-feners G and H.

These stiffeners were twisting very noticeably at 3-1/4 psi.

At 3-1/2 psi, stiffeners G and H had about a 1/2" bow.

At 4.26 psi, stiffener E failed followed by stiffeners F and D.

Secondary failure of upper corner between stiffeners D and E developed.

Then stiffeners C and B buckled and a leak de-veloped.

5.2.4 Round Duct:

32" diameter The round duct was pressurized in 1/2 psi incre-ments.

After each increment, a visual inspec-tion of the duct was made to locate any areas of untypical behavior.

Nothing unusual was found.

At 4.53 psi, the duct suddenly collapsed i{)

into a triangular shape at center.

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6.0 Conclusions l

s-l 6.1 The duct tests showed that the failure pressure of each test specimen was at least 2.3 times greater'than

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the maximum pressure differential applied to the ducts following a loss of coolant accident.

The effects of seismic loading on the ducts, which are discussed in section 6.2, are small.

Therefore, a factor of safety of approximately two (2) is considered to be a reason-able and conservative margin to insure the integrity of the system under the combined 'ffects of pressure and seismic loading.

The ducts comprising the Reactor Building cool air supply duct system can be separat^ed into five main categories which are presented in Table I, page 12.

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The most critical duct in each category, which is the duct having the largest dimensions and' stiffener spac-ingc and the smallest stiffener size, represents the actual duct specimen tested.

The tested ducts, there-fore, represent the minimum acceptable requirements for the "as-built" conditions of each category of ducts listed.

6.2 Seismic stresses for the maximum earthquake condition were computed for the 35" X 30" duct specimen and are presented in Appendix C.

This duct showed the lowest collapse pressure of all the duct test specimens.

It should be noted that the stresses and strains are small and are largely confined to the duct skin mcterial.

It is therefore concluded that seismic loads on the duct stiffeners, which are the critical elements under pressure loading, are minimal and can be safely neg-f) lected as a contributing factor to duct collapse.

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'6.3 The duct elbows tested were equirped with turning vanes.

Since no failure or significant distortion of these elements was observed, no additional reinforcement is considered necessary.

6.4 No failures of the welds between the stiffeners and the duct sheet were observed.

Therefore, the welding on the tested duct specimens is considered to be hde-quate.

Based on the test results, the minimum require-ments for the stiffener duct sheet welds are as fol-I lows:

60" X 40" Duct 1/8" X 1-1/2" fillet weld at 6" on center spacing All the Rectangular Ducting 1/8" X 1-1/2" fillet weld at 8" on center spacing All Circular Ducts 1/6" fillet weld all around 7.0 Corrective Action The duct test specimens represent the minimum acceptable require-ments for the "as-built" conditions of each category of ducts.

The "as-built" conditions of the cool air supply ducts were de-termined by a field survey.

The data from this survey is given in Figures 7 through 11 and Appendix B.

Based on the field sur-vey and the test results the'following action will be implemented to ensure the structural adequacy of the ductwork:

7.1 Stiffeners will be added to the ducts as required in order to obtain a stiffener spacing equal to or less than the minimum acceptable requirements outlined in

! O Table I.

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r 7.2 The welding between stiffeners and the duct sheet'will be reinforced'as required to obtain a weld capacity equivalent to that of the duct test specimens as out-lined under Section 6.4.

7.3 Duct transitions will be reinforced to compensate for-

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the additional loads induced on the existing stiffeners due to changes in duct configuration.

7.4 All duct elbows not equipped with turning vanes will be stiffened.

7.5 Plenum will also require reinforcement.

Analytical methods will' be used to determine extent of stiffening required.

(p 7.6 Design drawings will be issued to implement the cor-rective actions outlined in the foregoing sections.

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R TABLE I DUCT DESIGN REQUIREMENTS AND TEST RESULTS Maximum Differential Pressyge Factor of Sa(ety er Stiffener Stiffener (P. S. I. )

Test Pressure Category Duct Size Angle Size Spacing Design (LOCA)

Test Design Pressure (in.Xin.)

I 17X12 1XIX1/8 48" 1.0 20X12 1XIX1/8 48" 1.0

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20X16 1XIX1/8 48" 1.0 5.42 5.4 II 30X23 1XIX1/8 32" 1.1 See Section 4.4 30X30 1X1X1/8 32" 1.2 lfj/

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III 30X20 2X1 2X1/8 32" 1.0 f

35X30 1

4X1 4X1/8 32" 1.2 2.82 2.3 IV 52X16 2X2X1/4 24" 1.3 60X32 2X2X1/4 24" 1.2 60X35 2X2X1/4 24" 1.3 60X40 2X2X1/4 24" 1.2 2.86 2.4*

V 12" Dia.

Stiffeners at hanger 1.0 14" Dia.

locations only.

Maximum 1.0 16" Dia.

hanger spacing 12'-0",

1.0 I

20" Dia.

1.1 32" Dia.

1.3 4.53 3.5

Duct not tested to failure

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,l REPORT OF PHYSICAL t

TESTS OF STEEL AIR DUCT FOR:

The General Air Conditioning Company 8107 Interstate 30 Little Rock, Arkansas 72209 Attn: Mr. Jim Wellons, P.E.

COPIES TO:

2-Above l-McCroskey Sheet Metal, Inc.

3200 S. Ceds Little Rock, Arkansas 72200 l-McNutt-Schneller j

Wallace Building Little Rock, Ark 5nsas 72201 l-Bechtel Power Corporation P.O. Box 459 Russellville, Arkansas 72801 Attn: Mr. Larry Tilley p>.

>k<

PURPOSE:

The purpose of this test procedure was to physically test a ten (10) foot long section of steel air duct by reducing the internal pressure below atmospheric to creata an external loading.

Two p6ints of deflection were measured and observations at various differential pressures were made.

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,p PROCEDURE:

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A ten (10) foot section of duct with four intermediate 2x2 inch angle supports was the subject of this test.

The duct specimen had steel sections welded across each end to create an air tight box.

This " box" was placed in a vertical position, long dimension vertical, and connected to a vacuum pump at the lower end and a differential mercury.

monometer near the top.

By creating a partial vacuum 4

internally, the duct section'was subjected to stresses created by atmospheric pressure.

The difference between internal and external pressures was measured on a differential mercury monometer.

The monometer accuracy was within one millimeter corresponding to a pressure of O'.019 psi.

RESULTS:

(

MONOMETER PRESSURE SHORT SIDE LONG SIDE READING (jPSI)

GAGE #1 GAGE #2 f

(CM)

- 0.019)

(INCHES )

(, INCHES) 30.2,30.2 = 0.0 0.0 0.800 0.900 30.5,29.9 = 0.6 0.116 0.611 0.870 31.0,29.4 = 1.6 0.309 0.508 0.820 32.1,28.3 = 3.8 0.735 0.450 0.738 33.0,27.4 = 5.6 1.083 0.407 0.683 33.9,26.5 = 7.4 1.431 0.310 0.540 35.0,25.4 = 9.6 1.857 0.212 0.497 37.6,22.8 =14.8 2.862 33.9,26.5 = 7.4 1.431 0.458

Readings not recorded for safety reasons.

Observer was too close to duct and failure might result in injury.

- Gage' mount had moved; reading inaccurate.

CONCLUSIONS:

1. The sub' Ject duct did not fail or collapse in any way.

f 1,

2. There was noticeable diaphram type deflection of the J.

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sheet metal between stiffeners under final load.

3. There was noticeable deflection-of the 2 to 2" steel angle along the long side of the duct at the duct m'id point under final load.

4. All noticeable load-created deflections were recovered after load removal.

5. No welds failed.

6. This method worked very well as a test procedure j

and it is felt that the test is a reliable method of testing these types of. ducts.

It is felt that this procedure will carry the duct to failure if required.

A WELD MEASUREMENTS:

(

The attached work sheets are measurements of lengths and spacings of stitch welds connecting 2 x 2 angle braces

/

to sheet metal duct.

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REPORT OF: STRUCTURAL DUCT TESTS (DESTRUCTIVE)

PROJECT:

POST RECOVERY DUCTS ARKANSAS NUCLEAR ONE RUSSELLVILLE, ARKANSAS PURCHASE ORDER HUMBER: GAC 19 FOR:

GENERAL AIR CONDITIONING CORP.

8107 INTERSTATE 30, FRONTAGE ROAD P.O. BOX 9219 LITTLE ROCK, ARKANSAS 72209 REPORTING:

NO. OF COPIES (2)

ABOVE (4)

BECHTEL POWER CORPORATION P.O. BOX 459 RUSSELLVILLE, ARKANSAS 72801

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LABORATORY NUMBER: LR-79773 DATE: FEBRUARY 27, 1974

s SAnfMlPuy-AGEE LASONATOmsES. GNC.

I EIHIBITS NUMBER 1 - Bechtel Power Corp. Specifications for Duct Testing.

NUMBER 2 - Data on Model 1200 Strain Indicator.

NUMBER 3 - Data on Model 1225 Switching and Balancing Unit.

NUMBER 4 - Calibration Certificate of Strain Indicator.

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NUMBER 5 - Strain Gage Data.

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f-l STRUCTURAL DUCT ;.'EST v

The purpose of this test was to observe the behavior of typical sections of reactor buildir.g air supply ducting under reduced internal pressure and to make strain measurements to determine failure mode, pressures and strain values. Information concerning the procedure and methods used are found in Bechtel Power Corp. Specification, " Test Procedure for the Vacuum Pressure Testing of the Reactor Building Air Supply Duct Specimens of the Arkansas Nuclear One, Unit #1 for the I

Arkansas Power and Light Company", copy enclosed as Exhibit 1.

The following is pertinent data which is applicable to all tests performed:

1. Date of Testing: 2-21 and 2-22, 1974

2. Deformation Reading: Dial gages (Ames type) -0.001 inch f

accuracy.

3. Structural Strain Measurement: BLH Model 1200 Digital Strain Indicator BLH Model 1225 Switching 8 Balancing Units Exhibit 2 and 3

4. Equipment Calibration Certificate:

(Exhibit 4)

5. SR-4 StrainGages equivalent to those indicated in specifications were used and information concerning these gages is listed as Exhibit 5.

6.~A mercury manometer was used to record all vacuum presures.

7. 8 mm (Super 8) movies were made along with 35 mm color pictures of all duct testing. These pictures will be sent at a later date under separate cover.

-,q SAEMBOW.AGER LAGOAATCaese. Ipec. _.

8. All strain gages were connected to the same channels for all tests. The following is the sequence used:

CHAreNEL STRAIN GAGE 4

1 1 - As Shown in Specs.

2 2

do 3

3 do 4

4 do 5

5 Longitudinal 6

5 8 450 7

5 Transverse 8

6 Longitudinal 9

6 Transverse 10 7

Lon#itudinal i

11 7

Transverse 12 8

Longitudinal 13 8

8 45o 14 8

Transverse 15 9

16

0 age 16 was used on ducts - Test 2 and Test 3 as follows:

1. Test 2, Center of Span, 0.25" from top of vertical leg of angle, 3rd bracket from end of duct where gage 1 is on bracket number 1.

/

2. Test 3, Center of Span, 0.25" from top of vertical leg of angle. 3rd bracket from end of duct where gage 1 is on bracket number 1, ie, on opposite leg from gage 2.

9. Dial gages were placed as indicated in specifications without exception.

10. The following are the ducts tested along with internal failure pressure:

INTERNAL PRESSURE TEST DUCP AT FAILURE 1

20" x 16"

-5.k2 psi 2

35" x 30"

-32"

-2.82 psi Spacing of Brackets 3

35" x 30"

-16"

-h.26 psi Q

Spacing of Brackets 32" Round

-4.53 psi l

BA8HDOW-AGEE LASONATOSHSS. INC.

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11. The ducts tested failed in the following mode:

TEST FAILURE MODE 1.

Compression Failure of angle bracket approximate center of long side (20")

on bottom of duct.

2.

Compression Failure of angle bracket number 3 from gage 1 end, approximate center of long side (35") on top of duct.

Failure was ven near strain gage #16.

3.

Compression Failure of angle bracket number 3 and 4 from gage 1 end, approxi-mate center of lo,ng side (35") on top of duct.

b Failure very near strain gage #16 Q

,k.

Invard collapse of longitudinal seem weld along approximate center one-third

/

of duct. Generated total collapse.

12. Results of strain gage readings are presented in micro inches /

inch and dial gage readings are those readings actually recorded in inches. Dial gage readings indicated gs posit've are inward i

movement of the measured member and negative readings are outward,

Positive (+) strain gage readings are tension and negative (-)

readings are compression. The results of all strain gage readingu and dial gage readings with their corresponding vacuum pressures are presented as follows for each duct:

J

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Q DUCT #1 STRAIN GAGE READINGS - MICR0 INCHES / INCH CHANNEL LOAD 1

2 3

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6 r

8 9

10 n

12 13 14 15 0.00 0

0 0

0.25 8

13 16 7

35 39 58 7

69 32 62 99 2k 49 3

0 50 13 73 Tk 17 44

-129

-503 26 325 9h 302 152 39

-59 2

0 75 -16 67 n1 17

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-585 n

412 96 h25 170 18

-87 10 1.00 -53 57 125 26

-03

-372

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-72 381 60 480 255 203 184

-82 1.25 -69 50 n6 9

33

-387

-829

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-13

-97

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-b 45

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-76 924 50

-39

-146 M

l 1 75 -84 33 125 3

96

-488

-n96 -87 929

-98 999 134

-43

-225

-10h 2.00 -95 0

109

-3 138

-531

-1303 -145 1037

-n7 1077 198

-69

-3 46

-106 2.25 -105

-n n5

-10 197

-562

-1369 -196 n32

-13 9 n80 229

-n8

-481

-98 2 50 -nB

-38 103

-18 234

-575

-1414 -227 1257

-164 1294 2 Sk

-227

-717

-llh 2 75 -129

-79 87

-27 270

-5Th

-1451 -270 1325

-202 135T 276

-255

-807

-124 3.00

-1 32

-n8 32

-In 323

-580

-1514 -334 1415

-262 1h3h 318

-285

-930

- 150 3.25

-1 45

-160 7

-14 9 3 67

-583

-1566

-399 1492

-323 1502 3 54

-314

-103T

- 194 3 50 -159

-213

-6

-38 2 bl9

-585

-1623 -468 1 595

-385 1584 4 02

-383

-1 239

-192 4.00 -183

-296

-n

-455 510

-586

-1704 -599 1704

-504 1667 500

-437

-1452

-247 4.50 -194 4 04

-100

-583 602

-574

-1778 -736 1793

-627 1745 608

-490

-1 673

-295

]l 5.00 -216

-535

-223

-7 20 6 88

-566

-1843

-867 1 867

-747 1810 7 13

-530

-1868

- 337 PAIL-JRE*

251

-n81

-6

-278 1098

-787

-3462 -15h 2806

-1089 22k5 h20

-27kk -9707

-302

'The readings at failure are after structural, failure had occurred, but the failure pressure was maintained.

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DUCT #1 DIAL OA0E READING - INCHES LOAD A

B C

D E

F G

H J

K 0.00 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.25 0.045 -0.018 0.096 0.011 0.0k5 0.015 -0.005 0.006 0.075 0.001 3.50 0.372 -0.199 0.128 0.092 0.340 0.075 -0.048 -0.029 0.142 -0.078 0 75 0.452 -0.136 0.145 0.091 0.k20 0.112 -0.058 -0.031 0.200 -0.100 L.00 0.551 -0.087 0.059 0.096 0.715 0.190 -0.120 -0.153 0.270 -0.070 1.25 0.603 -0.078 0.065 0.089 0.778 0.187 -0.074 0.067 0.470 -0.072 L.50 0.663 -0.060 0.076 0.084 0.903 0.214 -0.057 0.122 0.513 -0.025 L.75 0 701 -0.ohl 0.085 0.089 0.949 0.225 -0.0h0 0.165 0.540 0.063 2.00 0 750 -0.031 0.099 0.089 1.000 0.242 -0.028 0.214 0.585.0.160 2.25 0.789 0.125 0.110 0.090 1.043 0.255 -0.008 0.266 0.633 0.220 e.50 0.840 0.182 0.121 0.089 1.088 0.270 0.023 0.375 0.677 0.266 2 75 0.878 0.251 0.130 0.091 1.129 0.287 0.038 0.423 0.713 0.400 3.00 0 937 0.310 0.160 0.122 1.203 0.317 0.071 0.500 0.T71 0.450 3.25 0.994 0.365 0.175 0.120 1.265 0.359 0.085 0.555 0.820 0 492 3.50 1.061 0.438 0.199 0.123 1.338 0.389 0.108 0.649 0.878 0.526 I

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v-DUCT #2 EFFRAIN GAGE READINGS - MICR0 INCHES / INCH LOAD 1

2 3

4 5

6 7

8 9

10 n

12 13 1h 15 16 0.00 0

0 0

0 0.25 -25

-33

- 46 3

-33 0

-19

-312 196

-35 260' 1 31 2 40

-50 6

-218 i

0 50 -41

-72

-64

-64 82

-99

-32

-n89 5 02

-n 6 5 90 665 185

-262 35 483 0 75 -k9

-98

- 161

-86 226

-67

-161

-2040 6 05

-191 7 h5 815 2n

-378 38 926-1.00 -79

-81

-565

-132 269 91

- n 3.

-1724 683

-270 1 000 8 94 2 79

-456 14 4190 1.25 -8 6

-104

-679

-221 250 147

-71

-2707 8 07

-kn 1 255 901 3 22

-508 49

-1520 i

1.50 -82

-1 35

-646

-250 187 198~

h

-2997 9 54

-666 1417 8 66 297

-533

-kT

-1752 1 75 -118

-182 G age

-250 183 203

-n

-2818 1 062 -801 1 656 82 6 2 80

-565

-82 4940 2.00 -145

-225 O ut

-277 179 203

-2;

-2795 1 13 1 -865 1 759 795 2h7

-592

-112 - 2111 2.25 -180

-2 81

-306 180 20h

-36

-3179 1301 -916 1 871 758 2 12

-615 4h6 -2276 2 50

-2 07

-396

-33 1 195 201

-65

~3616 1 h31 -949 1 970 725 1 85

-629

-202 - 2432 2 75 -230

-959

-368 206 21

-312

-4218 1 997 -1007 2h63 705 112

-760

-242 -2b29 1

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DUCT #2 DIAL GAGE READING - INCHES LOAD A

B C

_D E

F G

H J

K 0.00 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.25 0.143 0.057 0.025 0.014 0.145 0.014 0.022 0.140 0.138 0.063 0.50 0.210 0.123 0.049 0.04k 0.351 0.022 0.078 0.445 0.k18' O.086 0.T5 0.250 0.170 0.075 0.065 0.k44 0.035 0.092 0.5ko 0.730) 0.118 L.00 0.315 0.220 0.n5 0.085 0 555 0.053 0.095 0.608 0.813 0.160 L.25 0.358 0.258 0.137 0.106 0.6kk 0.075 0.100 0.675 0.893 0.202 L.50 0.390 0.295 0.162 0.120 0 747 0.096 0.10h o.T18 0.940 0.242 L.75 0.433 0.320 0.191 0.136 0.823 0.110 0.n2 0.789 1.000 0.279

!.00 0.470 0.350 0.219 0.1k5 0.886 0.121 0.117 0.828 1'.054 0.308 2.25 0.5n 0.382 0.250 0.154 0 952 0.134 0.2.25 0.870 1.n5 0.339 2.50 0.550 0.409 0.293 0.161 1.019 0.147 0.135 0.903 1.187 0.365 U

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DUCT #3 STRAIN GAGE TtEADINGS - MICR0 IFCHES/ INCH IDAD 1

2

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5 6

7 8

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12 13 14 15 16 0.00 0

0 0

0-0 0

0 0

0.25 19 2h 30 23

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-52

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-13

-In -145 48 121 31 78

-21

-51

-70

-6

-204 0.75 -2k 60 77 66

-7

-193 -288 80 201 51 138

-23

-56

-85

--15

-340 1.00 -37 124 n8 ST' 20

-164 -316 80 ' 251 53 200

-38

-22

-8

-15

-591 1.25 46 12h 1 56 81

-43

-191 -208 103 340 59 260

-49

-34

-26 40

-700 1.50 32 n6 180 40

-41

-203 -244 81 750 -271 819

-1035 -537

-173

-40

-817-1.75 69 116 1 98 26

-60

-128 -171 73 813 -309 836

-1054 -552

-169

-81

-1015 2.00 46 140 285 15

-258 -86 n

-5 in8 -185 1089

-1040 -541

-153

-90

-1205 2.25 33 1 30 309 0

-333 -120 33

-202 1 229 -181 1277

-1019 -5k0

-171

-In

-1320 2.50 9

1 07 302

-18

-347 -121 45

-277 1317 -233 1375

-1019 -Sko

-160

-122

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2.75

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-26

-351 -nk 67

-333 1400 -280 1k61

-1020 -540

-147

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-35

-359 -112 78

-392 1458 -330 1 530

-1019 -539

-137

-165

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-439 1526 -380 1602

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-122

-181

-1865 3.50 -95 13 2 88

-59

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LOAD A

B C

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K 0.00 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 o.25 0.023 0.021 0.018 0.006 0.040 0.002 0.000 0.010 0.C20 0.020

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0.50 0.048 0.052 0.036 0.015 0.091 0.003 0.009 0.03h 0.049 0.0k0 O.75 0.09k 0.076 0.065 0.025 0.169 0.006 0.013 0.050 0.109 0.060 1.00 0.099 0.099 0.100 0.022 0.192 0.014 0.004 0.037 0.300 0.093 1.25 0.182 0.n5 0.120 0.033 0.199 0.017 0.007' o 050'.0.489 0

0.217 1.50 2n 0.138 0.140 0.091 0.251 0.020 0.091 648 40.533 0.241 1 75. 225 0.161 0.174 0.101 0.340 0.023 0.099 0.670 0.570 0.268 2.00 0.260 0.175 0.2n 0.105 0.427 0.040 0.025 0.675 0.595 0.285 2.25 0.288 0.194 0.231 0.n5 0.466 0.080 0.059 0.625 0.623 0.305 2.50 0.314 0.2n 0.250 0.124 0.496 0.094 0.063 0.692 0.652 0.325 2 75 0.319 0.227 0.269 0.132 0.524 0.106 0.066 0 710 0.680 0.3kk 3.00 0.366 0.243 0.286 0.14 1 0.552 0.n8 0.072 0.726 0.710 0.361 i

3.25 0.392 0.261 0.306 0.152 0.581 0.130 0.078 0 745 0.740 0.379 3.50 0.k22 0.281 0.331 0.164 0.616 0.137 0.085 0.764 0.772 0.398 3 75 0.461 0.296 0.378 0.174 0.666 0.157 0.091 0 780 0.813 0.413 i

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i l-TEST PROCEDURE I

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for the VACUUM PRESSURE TESTING OF THE j

REACTOR BUILDING AIR SUPPLY DUCT SPECIMENS of the i

ARKANSAS NUCLEAR ONE UNIT #

1' j

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for the i

ARKANSAS POWER AND LIGHT COMPANY r

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l Consisting of:

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Test Procedure - - 3 pages i

General Notes I

l Figures 1 through 6

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Purpose of Test V

The purpose of this test is to observe the behavior of typical sec-tions of the reactor building air supply ducting under vacuum pres-sure, and to determine from these observations whether or not further modifications to the reactor building air supply ducting are required.

4 II.

Test Description The test shall consist of applying increments of vacuum pressure to each of the four test specimens shown in Figures 1 through 4, and measuring the stra'in and deformation response of the specimen at each pressure increment.

The pressure shall be increased in incre-ments of 0.25 psi until the specimen fails.

The following specimens shall be tested:

1.

A section of rectangular ducting, 20" X 16", with a 90"

(N elbow, and angle stiffeners around the circumference of the duct at

\\I 48" spacing.

(As shown in Figure 1.)

2.

A section of rectangular ducting, 35" X 30", with a 90* el-bow, and angle stiffeners around the circumference of the duct at 32" spacing.

(As shown in Figure 2.)

3.

A section of rectangular ducting, 35" X 30", with a 90*

1 elbow, and angle stiffeners around the circumference of the duct at 16" spacing.

(As shown in Figure 3.)

4.

A section of circular ducting, 32 inches in diameter X 12 feet long.

(As shown in Figure 4.)

III.

Test Preparation A.

Test Specimens The test specimens shall be in the horizontal position res-ting on support blocks located as shown in Figures 1,

through 4.

Thin stripes shall be scribed on panels of the ducts prior to testing for the purpose of observing differential movement during the test.

Alter-j nate panels shall be striped in one direction and intermediate panels (sY

\\._.)

-=-

t

. f) shall be striped in a perpendicular direction.

'~'

The test specimens shall be leak tested before testing.

An internal pressure of no greater than 1/2 psi shall be used during leak testing.

B.

Instrumentation 1.

. Strain gages Strain gages shall be mounted to the test specimens at the locations shown in Figures 1 through 5.

Single element strain gages shall be Micro Measurements type EA-06-125AD-120 or equal.

Double element strain gages shall be Micro Measurements type EA 125TM-120 or equal.

Rosette strain gages shall be Micro Measurements type EA-06-125RA-120.

1 Strain gages shall be mountc; to the test specimens using. Eastman 910 adhesive, Micro Measurements M-Bond 200, or other equal adhe-sives.

(^'s A thin coat of waterproofing shall be applied to each gage after it k-l has been wired to the readout equipment.

The waterproofing shall be flexibic in nature such as Micro Measurements )! coat A, M coat C, or other equal waterproofings.

~

A three conductor cable shall be used to wire the strain gages to the readout equipment.

The readout equipment shall consist of a switch and balance unit and a strain indicator.

2.

Dial gages Dial gages used for measuring deformation shall be accurate to.001 in and shall have a travel 71 :".

They shall be placed in contact with the test specimens at the locations speci-fied in Figures 1 through 5.

Dial gases shall be mounted to a rigid frame which is independent of the test specimens.

3.

Pressure Gage (j,%,

Vacuum pressure in the test specimens shall be measured

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* ~ ~

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- C using a mercury U tube manometer.

IV. Data Acquisition Prior to the start of the test, each test specimen shall be sub-jected to a vacuum pressure of 1/2 psi in order to remove any outward curvature of the specimens caused by application of internal pres-sure during leak testing.

The vacuum pressure shall then be re-leased and zero readings taken on the deflection and strain gages.

Deflection and strain data shall be obtained at 1/4 psi increments of vacuum pressure until the specimen fails.

At each increment of pressure, a v'isual examination of the test specimen shall be made to locate any arcas of possible stress concentration or to note any other unusual behavior.

V.

A test report shall be prepared showing all pertineat data and test results.

VI.

8mm slow motion films sh'.11'be taken of all' duct specimens during the vacuum pressure test.

Films shall fully document duct behavior during the testing and failure stage.

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GENERAL NOTES

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All duct specimens shall be fabricated in accor-

"5c h8 dance with specification 6600-M-52A and Figures 55 jj 1,2,3,4,5, and 7 of this test procedure.

NSE*

e*E 33 2.

All stiffener angles and closure plates shall be Tj 22; ASTM A-36.

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All ducting material shall be ASTM A-525, 14 gage (C24LV.57 EEL)

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4.

All specimens shall be tested in the horizontal

!Y yj position.

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All 90' elbows shall have turning vanes z _e

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BLH ELECTRONICS,INC. i MODEt ms SWITCHING AND BALANCING UNITj

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Product Data 608 Effective knucif, '.

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i SPECIFICATIONS Inputs:

%. % and full bridge circuits Additional Channels:

or strain gage transducers, Urits may be stacked and inter. j e

connected to obtain 20,30,40, a Gage Resistances:

60,120, 350, 500 and 1,000 fofnts*

ohms on full bridge. 60 2.000 ohms on half bridge.

Gage Connections:

Ten, five terminal grocps to-Controls cated on front panel. Gages a

X may be connected to the instru.

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ment in active compensating Poterytiometers:

1 per channel.

pairs - groups of actives with Gage Resistance a common compensating, or Switch:

HB, 60,120, 350, 500 and any desired combination includ.

ing three wire lead systems.

1,000 ohms FB.

Channel Selector Balancing:

By means of balancing poten-1 Switch:

Ten Positions plus "Off".

4 tiometers with special friction drive zero adjustment requiring no locking. Full balancing range 1

of 2 7,000g"/"

Size:

s 97/s W x 7% H x 13% D(with cover).

j Repeatability:

B, etter than 1.0 microinch per inch repeatability for 5 x 105 Weight:

8.25 lbs. (with cover) switch rotations.

Temperature Range:

32 to 130'F (0 55'C) e I

l eEXHIBIT NUMBER 3 a

BLH ELECTRONICS,INCe A subeldiary of Baldwin e t.ima e Hamliton Corporation WALTHAM, MA3SACHUSETTS 02154 Twx: rio4244sas nu.m e244is cAaLE: **BAUMA" speciscatens subject to change evithout notice i

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BLH ELECTRONICS, INC.

42 FOURTH AVENUE. WALTHAM. MASSACHUSETTS 02154 ARLA CODE 617 890 6700 CERTIFICAIE OF INSPECTION CUSIOMER DATE #

CUSTOMER'S ORDER NO.

BLH S/O NO.

THIS IS TO CERTIFY THAT:

The instrument (s) listed has been run at an elevated j

tempera ture (130*F) and under operating conditions.

This instrument (s) has satisfactorily passed this. test and final tests and is within specifications.

MODEL NO.

FUNCTION SERIAL NO.

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BLH ELECTRONIC 5, INC.

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Il ~ 9 4 f l k I 1 .I O APPENDIX D' 1 I I I I P l i i 1 I f f ( i 1 l I i l-' i 4 I l-t 0.. w h

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ML19326B510

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