three mile island nuclear station, unit 1, revision 24 to ... · ,j ii• ~ t 'i ~ ir 1 1\ 11...

$: Three Mile Island Nuclear Station, Unit 1, Revision 24 to ... · ,J II• ~ T 'I ~ Ir 1 1\ 11 IIWM++, ~ I:l I 11 l n-.... ~ ~ ~-100 1.6 1.2 •o ~ ~ 1.0 a c o ~ u ~ z ~a 0.1)(c 2$
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Update -1

7/82

p.5A.FIG-l Total Reaction vs Time Curve

Fig.5A-l

1

~ _WINGS & ENGINES

J \- ATTACHED

h \~J \V

~WINGS & ENGINES

,JI""DETACHED

j \I \ \• .....

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7/82

p.5A.FIG-2Load Time Curve for 720 Aircraft at 200 Knots

Fig.5A-2

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0.2 0.3 O.~ 0.5 1.0

ra:im Nuclear1MI Unit-'

Update -,7/82

p.5A.FIG-3

Maximum Dynamic Load Factor vs Period orFrequency of a One-Degree-Freedom System underthe Impact of Boeing 720

Fig.5A-3

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C II'it

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Spherical Cap under a Ring Load

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7/82

p.5A.FIG-4 Fig.5A-4

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Update -1

7/82

p.5A.FIG-5Spacial and Time Distribution of Load on Shell

Fig.5A-5

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~Nucl..r1MI Unit-l

••;

1ft•62

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o

Update -1

7/82

p.5A.FIG-6

Grid for Dynamic Finite Element Analysis of AircraftImpingement on Dome

Fig. SA-&

)

0.1SECONDS

0.2 0.3

II

I

" NOTE: eKSI CORRESPONf)5, TO A LO D OF 5800 KIPS

(~ 20 )( E.1611T Of TII£ AIR-

VERTICAL D'SPL~CEMENT OFT"EIAPEX (BASED O~ ~= .lKS')

I~ .. 0.16 SEC' .,CASE @ TIt.1E Of LOADAPPLICATI$N

0.4

TIME AFTE~·BE INNIN6 OF IMP.I t. • 0

@)~I tJ. : 0.16 SEC

0.2 ' • 0.16 SEC

0.8 I ,

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z I , ta. II~C'" 0 I t. · 00

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Update -1

7/82

p.5A.FIG-8

Deflections and Stresses for Aircraft Impingementfor Time = 0.16 Seconds"Constant Deceleration

Fig.5A-8

350 .....----......----.....----.....----....

0.40.3

\

0.2

TIME-SECONDS

0.1

C-JJ9C---......

o~----.......----......---------........o

250 .....-----4------+--~~--+------I

50~----_+_----+_+_----_+_-~~-~

\\

100 ~----+-----4~_+_------+-_+----4I

300 ~-----+-----~r__-----+-----~

a

a "~ 200 .....------+---;.---+----""'--+------1V)..........towWLL.

I>to-

g 150 ~-----+--- ........--+-----......-----I~ \

\

Iai!J Nuclear1MI Unit-l

Update -1

7/82

p.5A.FIG-9Velocity Diagram for 720 Aircraft at 200 KnotsImpact Speed with Wings and Engfnes Detached

Fig. 5A-9

350 ....---~-----....---..........---.....

300 I------~----~~---_+_----_I

0.4G.!

..........._-0.2

TIME-SECONDS

0.10 .....----....----......----.....---........o

250

C-1l9C----.....a ",z0u 200w

\~~w ,W&L

I \>-~

U 1500-oJ

\w>

\\

100

\\\

50

[[il!] NuclearTMI Unit-1

Update -17/82

p. 5A.FIG-IOVelocity Diagram for 720 Aircraft at 200 KnotsImpact Speed with Wings and Engines Attached

Fig. 5A-l 0

IfJO 1101060

AIRCRAFT WEIGHT BREAKDOWN

FUSELAGE 51,000 LaEMPENNAGE 5,680NOSE GEAR 700, MAIN GEAR 5,380INB. ENG. 10,800OUTB. ENG. 10,300WING STR. 29,700

S113,560 LB

0 PASS. & BAGS 13,0008 CARGO 10,000-- FUEL 63,440... ---~ G. W•• 200,000 LB~ 4wc:L. ~ASS DI5l £ 70co-J LOSS f OU R POll. ION

IOFW 1J(jz

0~i=

:::>coa:...U)

is... 2isw~

I

DISTANCE - FEET

o 200 4{)() 60D 800

F.5.IfJOO IZOI '"10

B:iEl Nuclea,TMI Unit-1

Update -1

7/82

p. 5A.FIG-I1 720 Aircraft Mass 0 istribution

Fig.5A-11

-

7/

/ -

V -~

7 -

,~

-

-

----~

~ -~

~ -

-

-

-,",,-

I I I I ~Pa,..." CRUSHING LOAD IN POUNDS )( 10'

[aj[I NuclearTMI Unit-1

Update -1

7/82

p. 5A.FIG-12 Boeing 720 Fuselage Buckling (Crushing) Load

Fig.5A-12

r =0.0"

MAXIMUM DISPLACEMENTOCCURS AT CENTER OFDOME AT TIME t =.2 SEC.

41)

wJ:U!I

toZW~WU~

-'Q.

~Q

-'~UtoOl:W>

-2.0 -- r..- --& ...L. ---J

o 0.1 0.2TIME - SECONDS

0.3 o.~

lm1!I Nuclear1MI Unit-1

Update -1

7/82

p.5A.FIG-13 Time Variation of Shell Vertical Displacements withWings and Engines Detached

Fig.5A-13

.O~ ,...-----------------------------.

MAXIMUM DISPLACEMENTOCCURS AT CENTER OFDOME AT TIME t = .2 SEC.

,=0.0"-1.2

0t.~:::__-------------------..,-~--~....-4

-1.6

I/)

w];:UZ -O.~

I...zw~wu -0.8~-oJa..I/)

Q

-oJ~

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-2.0

o 0.1 0.2

TIME - SECONDS

0.3 O.~

[[iI!] NuclearTMI Unit-1

Update -1

7/82

Time Variation of Shell Vertical 0 isplacements withWings and Engines Attached

p. 5A.FIG-14 Fig.5A-14

MAXIMUM AND MINIMUM WINGS & ENGINES ASSUMED

PRINCIPAL STRESSES TO BE DETACHED FROM

AT THE TOP AND BOTTOM FUSELAGE

SURFACES OF THE DOME

2

;;;W

I

'"'" 0WI¥...'"WI¥A.

i -2~...U~A.

~ -~CJ...w

~

'" -6w

'"'"WI¥...'"Q -IwzCD MAXIMUM COMPRESSIVE STRESS20 IS 9372 PStu

-10

0 0.1 0.2 0.3 O.~

TIME - SECONDS

~Nuclear

1MI Unit-1

Update -1

7/82

p.5A.FIG-I5

Time Variation of Shell Surface Stresses Aircraftwith Wings and Engines Detached

Fig. 5A-15

2

0."0.3

BOTTOM SURFACE

MAXIMUM COMPRESSIVE STRESS

IS 9352 PSI

,=o·

0.2

TIM! - SECONDS

0.1

MAXIMUM AND MINIMUMPRINCIPAL STRESSES

AT THE TOP AND BOTTOM

SURFACES OF THE DOME

-10 .....------..&.-------.....------.....--------'o

v;~

I O .....-------------.'---;.--~-~P"""'""---------__IV)V)

wa:~V)

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ow~ -8co2oU

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Update -1

7/82

p. 5A.FIG-16

Time Variation of Shells Surface Stresses Aircraftwith Wings and Engines Attached

Fig. 5A-l &

FOURlEi SERIES =.Q7955· ,1575 COS, + .1558 COS 2'· .1"6 COS 3' + •\33 COS'"•. 1208 COS 58 + ~ 1058 COS 6' •.08CU COS 71 + .0722 COS 8'• .0551 COS 98

&o•

~Nucl..r1MI Unit-1

Update -1

7/82

p. 5A.FIG-I7Pressure Distribution for Aircraft Impact

Fig. 5A-17

020"1 r

Update -1

7/82lail!J Nuclea,TMI Unit-1

.75"

1129 FT·K/FT

~.\1'

+150 - ~

<<9140 - ~

0.-A130 - ~

120 -<0~~

110 -

100 -t-W 90-wu.• 80~to- 70~

>W.-oJ 60w

SO -40

30

20

10

0

MERIDIONAL MOMENTS .SHEARS DEFLECTIONSAircraft Impact at Girder to Dome Transition

p. SA.FIG-IS Fig. 5A-18

Update -1

7/82~NuclearTMI Unit-1

.....-1.04"326

K/FT150 _ --+-.............-..~ 998 FT-K/FT17.5 x 106 LB

(TOTAL LOAD)140 -

so -

130 -

30-

40 -

10 -

20 -

100 -

110 -

120 -

1616 FT-K/FT

...w 90wu.• 80zo

I- 70~

>~ 60-LIJ

0-

MERIDIONAL MOMENTS SHEARS DEFLECTIONSAircraft Impact at Spring Line

p.5A.FIG-19Fig.5A-19

Update -1

7/82

1.14 "

p. 5A.FIG-20

"

", ,\

\\,,I

//

/,/

-'""

ELEV.149'-1"

~NuclearTMI Unit-1

Radial Deflection Impact at Spring Line

Fig.5A-20

.127"l rI t

Update -1

7/82[ffi[1 NuclearTMI Unit-1

......- 1.00"

- 177 K/FT

184 K/FT

~ -226 K/FT14-- 1297

FT-K/FT

1658 FT-K/FT

150 -

140 -

130 -

120 -

110 -

100 -

t- 90-wwu.• 80 -

z0t- 70 -<>w 60 -...JW

50 -

40 -17.5 x 106 LB

30 -(TOTAL LOAD)

20 -

10 -

0-

MERIDIONAL MOMENTS SHEARS DEFLECTIONS Aircraft Impact at Grade

p. 5A.FIG-21Fig. 5A-21

z y

/

~~_a__

(a) GEOMETRY

(b) 51 X FORCE COMPON ENTS AT

NODAL POINT

tai!I Nuclear1MI Unit-1

Update -1

7/82

p. 5A.FIG-22Rectangular Finite Element

Fig.5A-22

Update -1

7/82Heat Exchanger Vault Moment DiagramFor the Roof Slab

[ffil!l Nuclear1MI Unit-1

thickness: 6-:'0

N--

MOMENT ENVELOPE

impact positio/IS

pn

along secflon A-A

F,,' V'~ cr,.';/co / .IP»pa.c~

Q. 5 oircrorf

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b. 5 momenTS

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•o..,~

HOn?I?,.,f

2,800

2,'00

2,40D

2.,200

2,000

/,800

'S "'ao/'400.~

""~ /,].00~

~ - /, roo\J.~

" 800,~

~ "00.\':::" 400

~t:: 200~

~~/

200

.~400i)

~ ftJooctJ

800

1,000

1,200

/,'100

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2,000


TMI UFSAR

Figures 5A-24 through 5A-25

Deleted

v

p. 5A.FIG-26

BimNuclearTMI Unit-1

Critical Aircraft Impact-Direction 1

Update -1

7/82

Fig.5A-26

IMPACT

DIRECTION <Dc==::C>

r -----A --.............._SEE TEXT

PG. SA-18

- ,f

--I- •I •

I ' •.~:, - - ,-. ~ ... '.

la:im NuclearTMI Unit-1

Update -1

7/82

p. 5A.FIG-27

Concrete Cover to Protect Against Aircraft Impact

Fig.5A-27

-- ------~ -, .--.-.-"

------ t'o... t-l --~~ .--.. - .-- ~.---- _.-~ ... ---I I f

I I II I II I

II I II If

I TYR II 15P~'N6'1

I II II II II I

I

8iI!l Nuclear1MI Unit-1

Update -1

7/82

-p. 5A.FIG-28Detail of Anchor Block

Fig.5A-28

IMPACT OlQECTION

A A

(a.)

lb)

I~-- ASSUMEC N. A..

0]!]NuclearTMI Unit-1

Update -1

7/82

p. 5A.FIG-29Prestress Stresses after Nine Tendons Fail

Fig.5A-29

8zo..uuJex6tu<Q.

~

~~.. 't'{)

ta:im Nuclear1MI Unit-1

Update -1

7/82

p. 5A.FIG-30Critical Aircraft Impact - Directions 2 and 3

Fig.5A-30

p. 5A.FIG-31

ta:iZ!l NuclearTMI Unit-1

Equal Spacing of Roof Tendons

Update -17/82

Fig. 5A-31

UPdate - J

7/82Do,.,. rendons-------

BUTTRESS

ir IMPACT

~ DIRECTION 0

---

--- -----

- ---

----- - -------------

---~..... - - - - - - ...... ---- .....- - - - - -- -- - -- --- - -- - - --- ---- ---- .....----------- ---- ----- -_..-----

~Nucl..rTMI Unit-'

Update -,7/82

Minimum Spacing of Hoop Tendons

p. 5A.FIG-33Fig.5A-33

ELEVATION

DUE TO A.IRCRAF"T)IMPACT

DU& TO L.OSSOF HOOPPRESTRESS

DuE To VEsctlCAlPfiEST2ESS

..

DUE TO HOOPPRESTRESS

DUE TO VEJCT'C~

PRESTRESS

•

E:LEVATION

DUE TO HOOPPRe:5aT~e:~S

\DUE. TO ArRCRAFT IMP~T

TO A.L. PRESTRE~S LOS~ OF' H P F>QE&TRESS

Iai!l Nuclear1MI Unit-1

Update -1

7/82

Comparison of Prestress Loading

p. 5A.FIG-34Fig.5A-34

I I II I 1

~I ir, I~I I~I Ie!'

~I~I~

~I I~

~! w !~w~r

J'~I~01

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1<1(10w

/ I~~

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~I 10 I~

51 I~ I~UI

VIe Ij

~I 1&1) 10C)

I~~I !~-.~

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{ Ie!' 'fI~)"" IS I~

V t ~ t '"~ \0.40.30.2

TIME· SECONDS

0.1

cs/r

r,'\S'(j....,- , I r;f- , I

::; . I ~!:: , I

1\./

U ' :/0. ,

:; , , ,.u , ! \..

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I

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,~ -~

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CALCULATED REMOTE

"G" LEVEL

90

80

70

C)

~ 60..JwUw0

w 50C)<I(...JW&I)

40::::>u.w~

0~ 30w~

20

10

0.40.30.2TIME· SECONDS

0.1

RIGID STRUCTURE

R{~

oo

20

15'0

2)(

co.J

e!'0 10~0..J

Z2~

U~W01:

5

SEE TABLE 5A-6, REACTION LOAD CALCULATIONSWITH WINGS & ENGINES DETACHED

la:im Nuclea,TMI Unit-1

Update -1

7/82Reaction Load and Fuselage Decel. (Calculated for720)


f~/ \I \

\~

~ \~V'"

V ,1\

0.-0.30.2

TIME. SECONDS

0.1

.......~

IV

l\ /I .

1/I 'C.119C (TEST)! I.

I rI, ,

jI,

./\~ I. I·· "l ~ I ~

I ~ , ,~I

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I l'.1 \,I / \\.

~. f I A20 (IALCULjTED)•

~I~ ' ...... ",~ I'" .,

oo

80

90

CALCULATED REMOTE"G" LEVEL

70

dI 60

.JwuwQ SOwC)~.JW.,. ..0::J&L

Wt-O

30~W0:

20

10

0."0.30.2

TIME. SECONDS

0.1

RIGID STRUCTURE,---.---.~

R ---+~-..-.

oo

20

-015

0-)(

a».J

gQ~ 100.JZ0t=u~W0:

5

SEE TABLE SA.7, REACTION LOAD CALCULATIONSWITH WINGS AND ENGINES ATTACHED

~Nucl..rTMI Unit-1

Update -1

7/82Reaction Load and Fuselage Decel. (Calculated for720)

Fig.5A-36

p. 5A.FIG-36

2

--- TOP SURFACE STRESS

---- BOTTOM SURFACE STRESS

MAXIMUM COMPRESSIVE STRESS:; 5268 PSI

r HOOP STRESS /",,---,_

}I (BOTTOM) /' '"' .......

-------~ .......~--- MERIDIONAL STRESS .....~-----TOP BOTTOM

~L

-8

-2

-6

aUJzen~ou

InQ..

I 0~wa::...InWa::Q....,...u~Q..

~

o...w~aInInWa::...In

-10

o 0.1 0.2

TIME - SECONDS

0.3 0.4

ra:imN~I..r1MI Unit-l

Update -1

7/82

p. 5A.FIG-37

Hoop and Meridional Stresses at 36 Inches from theEdge of the Load Area

Fig.5A-37

r = 115.2"

~I\ 1\tL '\~ \~ \

\ 1~I

MAXIMUM AVERAGE SHEAR STRESS ACROSS

SECTION = 482 PSI

SHEAR AT r = 145.2-= 354 PSI

UL T1MATE SHEAR STRESS FROM CHAPTER 26 OF ACI 318 = \I = 3.5~ +0.3 fpc

v=3.5x 10.1 +0.3. 1600=128 PSI) 354 PSI OK

la]!] NuclearTMI Unit-1

Update -1

7/82

p. 5A.FIG-38

Average Shear Stress in the Dome at the Timet=0.20 Seconds, Wing and Engines Remain Atuchedto FUHIaga

Fig.5A-38

r =115.2"

~I' I'"t:;L '\~ \a:: \

\ /II

MAXIMUM AVERAGE SHEAR STRESS ACROSS

Sf CTION =4&2 P~'

SHEAR AT , = U5.2"=354 PSI

ULTIMATE SHEAR STRESS FROM CHAPTER 26 OF ACI 31S=v=3.5K +0.3 fpc

v =3.5 • 70.7 +0.3. 1600 =728 PSI) 354 PSI OK

0i!jNuclearTMI Unit-l

Update -17/82

p. 5A.FIG-39

Average Shear Stress in the Dome at the Timet=0.20 Seconds, Wing and Engines Detached fromFuselage

Fig.5A-39

.JuIQoL

Iai!J NuclearTMI Unit-1

Update -1

7/82

p. 5A.FIG-40

FEM Model-Radial Stresses Due to Prestress andAircraft

Fig.5A-40

/' ,'"l~'V 0

\)Ci

0

o

Update -17/82

rai!l Nuclear1MI Unit-l

o'"

Q

o 0 ~ 0 I0'0 () ,0 0 L

=r--~==================================================================================~o~=-====-_.--_..---.--rta

~!

•~I r---------------------~' DOME SECT'ON

p. 5A.FIG-41Radial Stresses Due to Prestress and Aircraft Impact

Fig.5A-41

RADIAL TENSION ZONES

HOOP AND MERIDIONALCOMPRESSION ZONE

- -~ _ ~_~TENDON- - ~--_.~- -&TENDON

~---7''-------- G.. TEN DON

ci<~

'0-'~-

lmmNuclear1MI Unit-1

Update -1

7/82

p. 5A.FIG-42

Zones in Compression or Tension Due to Prestress ofAircraft Impact

Fig.5A-42

three mile island nuclear station, unit 1, revision 24 to ... · ,j ii• ~ t 'i ~ ir 1 1\ 11...

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