Jet Flow Analysis of Liquid Poison Injection in a CANDU ...
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KR0101273
KAERI/TR-1739/2001
Jet Flow Analysis of Liquid Poison Injection in a CANDU Reactor
Using Source Term
2001. 1.
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KAERI/TR-1739/2001
"DUPIC ^ £ 5 . <$%<%*% 7}"
2001. 1. .
: DUPIC
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KAERI/TR-1739/2001
CANDU
10555
1/4
CANDU
nfl-
fgfm-%:
27.8 m/s °)JL,
2*}%
fe 8000 ppm
l r-x
, r- 6 ^ o l l A i f e 3.711 cl ^S-oil rcj-s|- 1
5J-7]]
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KAERI/TR-1739/2001
Jet Flow Analysis of Liquid Poison Injection in a CANDU Reactor
Using Source Term
ABSTRACT
For the performance analysis of Canadian deuterium uranium (CANDU) reactor shutdown system
number 2 (SDS2), a computational fluid dynamics model of poison jet flow has been developed to estimate
the flow field and poison concentration formed inside the CANDU reactor calandria. As the ratio of
calandria shell radius over injection nozzle hole diameter is so large (1055), it is impractical to develop
a full-size model encompassing the whole calandria shell. In order to reduce the model to a manageable
size, a quarter of one-pitch length segment of the shell was modeled using symmetric nature of the
jet; and the injected jet was treated as a source term to avoid the modeling difficulty caused by the
big difference of the hole sizes.
The source term model of the inlet flow was validated against experimental data of gas jet
flow. The validation calculation has shown that the source term model reproduces experimental results
when the grid structure is properly determined around the source position. The source-jet model was
also validated against a real-jet model that directly solves for the jet flow around the nozzle hole. The
results have shown that the source-jet simulation agrees with the real-jet simulation if the radial grid
is generated by stretching for several grids.
For the analysis of an actual CANDU-6 SDS2 poison injection, the grid structure was determined
based on the results of two-dimensional real- and source-jet simulations. The maximum injection velocity
of the liquid poison is 27.8 m/s and the mass fraction of the poison is 8000 ppm (mg/kg). The simulation
results have shown well-established jet flow field. In general, the jet develops narrowly at first but stretches
rapidly. Then, the flow recirculates a little in r-x plane, while it recirculates largely in r- 6 plane. As
the time goes on, the adjacent jets contact each other and form a wavy front such that the whole jet
develops in a plate form.
This study has shown that the source term model can be effectively used for the analysis of
the poison injection and the simulation result of the CANDU reactor is consistent with the model currently
being used for the safety analysis. In the future, it is strongly recommended to analyze the transient
(from helium tank to injection nozzle hole) of the poison injection by applying Bernoulli equation with
real boundary conditions.
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KAERI/TR-1739/2001
• 1
2
ABSTRACT , 3
List of Figures 6
List of Tables 8
Nomenclature 9
l.i
1.2 ^-tfl • <q <a^^^t 121.3 <3^-§- ^ ^ ^ 13
2. -fr a- *H ^^€- is2.1 xltij|«J-^^3|- Vb - S.'i 18
2.1.1 ^itifl^Ai i8
2.1.2 VHr-S-l 192.2 O]A>5)- v$%q 20
2.2.1 Body^Fitted Grid 20
2.2.2 5?-I-5r£3Hl tfl'S: <>]#%• *M^ 20
2.3 <y-5ie|# 22
2.3.1 Pressure-Velocity Coupling ^ ^ - ^ 22
2.3.2 Rhie-Chow i f l ^ ^ 23
2.3.3 SIMPLER SIMPLEC ^ 3 1 ^ # 24
3. ^ T f l f - S.'fl ^ ^ ^ 7fl<i 283.1 S L l ^ • 28
3.1.1 1/4 fi.<i 28
3.1.2 ^ % H ^«!r ^flJi. S.A> 29
3.1.3 3*1- ^ ^ 30
3.2 7^^^- ^ j ^ . 7\~fr ^ ^ £A} 30
3.2.1 ?3%}2:& ^ A*\ 30
3.2.2 ^I<+ £3j- «lJ2. 31
3.3 ^•y^l^f-0!] t})^- real-jetsf source-jet « ] s 31 # • 31
3.3.1 3 * H r % ^S: 32
3.3.2 AA^ % 7-^ 4€- ^4 als 32
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KAERI/TR-1739/2001
4. ^ 3 1 ^ -fr^ ^ ^ £ * H 524.1 H.1 ^ Tfl-ti M 524.2 -8- ^ ^ £ ^ ^ 53
4.2.1 ^^g- ^ 3L^: 54
4.2.2 ^ £ &3L 3L% 54
5. ^ § 67
6. I K f ^T2" 4 ^ 68
^ - J l ^ ^ 69
Appendix 71
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KAERLTR-1739/2001
List of Figures
Figure
1-1 Reactor Assemble • 15
1-2 Schematic of Liquid Injection Shutdown System 16
1-3 Structure of CFX-4.3 Code 17
2-1 Finite Difference Grid for Physical and Transformed Computational Plane 26
2-2 SIMPLE Algorithm 27
3-1 Injection Nozzle 37
3-2 Schematic Quarter Model of Injection System 38
3-3 Source in Arbitrary Mesh Center 39
3-4 Comparison of Velocity Vector for Real- and Source-Jet Calculation 40
3-5 Calculation Domain of Free Jet 41
3-6 Grid Structure for Free Jet Calculation 42
3-7 Comparison of Axial Velocity Profile for Real- and Source-Jet
along Jet Direction 43
3-8 Comparison of Axial Concentration Distribution for Real- and Source-Jet 44
3-9 Percent Error between Prediction and Experiment 45
3-10 Two-Dimensional Domain for Real- and Source-Jet Calculation 46
3-11 Two-Dimensional Grid Structure for Real- and Source-Jet Calculation 47
3-12 Comparison of Velocity for Real- and Source-Jet in Radial
Direction (from Hole of Injection Nozzle) • 48
3-13 Comparison of Velocity Vector for Real- and Source-Jet 49
3-14 Comparison of Concentration Distribution for Real- and Source-Jet
in Radial Direction (from Hole Injection Nozzle) 50
3-15 Comparison of Concentration Contour 51
4-1 Schematic Diagram of 1/4 One-Pitch Model 57
4-2 Grid Structure for 1/4 One-Pitch Model 58
4-3 Velocity Vector for Five-Pitch Model in r-x Plane 59
4-4 Streamlines of r- 0 Plane 60
4-5 Velocity Vector by Poison Injection in r-x Plane 61
4-6 Pressure Distribution 62
4-7 Turbulent Viscosity Contour in r-x Plane 63
4-8 Turbulent Viscosity 64
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KAERI/TR-1739/2001
4-9 Concentration Contour in r-x Plane 65
4-10 Concentration Distribution in Radial Direction 66
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KAERI/TR-1739/2001
List of Tables
Table
2-1 Constants of Standard k-e Model 25
3-1 Comparison of Liquid Injection System and 1/4 Model 34
3-2 Source Term in Boundary Condition 35
3-3 Structure and Number of Grid for Radial Direction 36
4-1 Boundary Condition and Physical Properties 56
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KAERI/TR-1739/2001
Nomenclature
A area or chemical specie A
as, aw, &N> a$ coefficient in the discretization equation
B, Bu, Bv chemical specie B or matrix multiplier
C\, C2, Cp constant of the standard k— e model
Gi, G2 convective terms normal to grid cell boundary (Eq. 2-12)
/ Jacobian of the transformation
k turbulent kinetic energy
MB molar weight of specie B (Eq. 2-7)
m normal vector
P turbulent production term (Eq. 2-9)
P, P' ,P* pressure, pressure correction, and guessed pressure (Pa)
Rij Reynolds stress, pufu/
Sj source term for i components
Sc, Sp constant part and coefficient of <f>P in the linearized source term (Eq. 3-1)
T temperature ( °C, °K )
t time (sec)
U{, Uj, uk velocity for x, y and z components (m/s)
u/ , Uj fluctuation velocity for x, y and z components (m/s)
xt Cartesian coordinates, x, y, z
YA mass fraction of specie A
Greek Symbol
a, 0, y coordinate transformation parameters (Eq. 2-14)
F diffusivity for the arbitrary scalar <f>
8y Kronecker delta
§7), 8$ finite difference mesh spacings in {• and r) directions
in transformed plane
e turbulent energy dissipation
TjB viscosity of solvent B , (Eq. 2-7 , cp, 10"2 g/cm • s)
fx, nt molar viscosity and turbulent viscosity (kg/m • s)
Ok, <ye turbulent Prandtl number for the turbulent kinetic energy
and the turbulent energy dissipation
p density (kg/m3)
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KAERI/TR-1739/2001
r,y shear stress tensor (N/m2)
4> association factor of solvent B, dimensionless (Eq. 2-7)
or arbitrary variable (Eq. 2-11)
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KAERI/TR-1739/2001
1.1
±r 1978\i ^ ^ A S
£r 12,716 MWe ll t « . *]$= 1999^
45,484
Fuel In CANDU Reactors)
DUPIC (Direct Use of Spent PWR
$X^[2]. DUPIC ^<S^.
, DUPIC
DUPIC
3TO. DUPIC
CANDU (CANadian
Deuterium Uranium) DUPIC
CANDU
(LOCA, Loss Of Coolant Accident)
( 4 ^
3*11- W ° } CANDU
SDSl (Shut Down System number 1)4 SDS2 (Shut
Down System number 2)7} §^-?);T}. (Fig. 1-1 %£) SDSl gr #^7.f ^^Sf lS . o l f -^^ l 3}*1
^ - i - ^r^-H-^l^lfe" ^ > k SDS2fe ^M ^ ^ # ^ ? 1 ^-S" € < i 71-1-e]^- (Gadolinium
nitrate solution, Gd(NC>3)3 • 6H2O)-§: ^ ^ ^ l ^ l f e ^ - i : ^fl^^-jaL $j)&. z\- ^ ^ l ^ j ^ . ^ S - ^ ^
^ AECL (Atomic Energy of Canada Limited)-*)] *)
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KAERFTR-1739/2001
i ^ f e CANDU 3\Z}3,% Al-g-^fe- ^ 1 , 2 , 3 ? ! 43L7}<>\) - i ^ S ^ r } - . Qx}^ o]]u}*| o]-g-
l3E DUPIC ^<S5 .» CANDU. SDS2^ Aj^j ^ 3g7pi
-8-71 (calandria shell)S. ^ " S ^ E ^ - ^ l E H & t } . (Fig. 1-2 %^2) SDS2°ll
>1- i5}7) ^-5>^ JL#O.S. ^A^£) f e ^m-fi-*5i) ^-S-i : ^ ^ " 1 :
(1.5^.) ^ H # S . i | 7 l Bfll-e
1.2
(SDS2)o)l
fe Tennekes and
A]] <g^, ^ SEjl^ a o i <^^ (potential core region), ^ o l c g « (transitional
region), ^ } ^ ^ (similarity region)^ cfl^H
Rodi and Spalding[8]^ x}^- *flJL°fl ^-g-«|-7l ^ § } ^ ^^.oflui^] (k)S]- ^Q°] (L)
] 1 - FLUENT 3 H h | f lHinze and Zijnen[10]<>l
^7 Spalding[ll]ol
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KAERI/TR-1739/2001
1966\i Oak Ridge National Laboratory (ORNL)
31 & 4 - ^T^Pressurized Water Reactor,
l-o SDS2S. ^}-§-«r31 Slty. °A
Water Reactor)^ >H ^H-^M, ^ r f e € # 7
CANDU € -
a ^ €^>.SDS2S] ^ 7
£6)1 A ^ 5
4 s . ^^l^lf-^l t|)fr iL:a*)[i3;
3.$\ ^t-S-S.7]- $^ -50 mkS. «>-
flnfl^^[14]6l| t r f^^ , 1^71-1-i
|tfl -400 mk, 4000 ppm^ S . o
PWR)fe tn^.^-
! ^ 1 ^ ^ ^ ^
§-£7> t^^ l fe
fl^fe- ^tfl -200
SDSl^l
CANDU
r-^IS. A
7> o l ^
\ A^slmk^>^l
BWR (Boiling
nfl 1.5
8000
1997\i t l S . IGCAR (Indira Gandhi Centre for Atomic Research)^]-Hfe- Nawathe
SDS2°11
4 * -fV* Sl^r. ^ ^ CANDU
1.3
SDS2S]
CFX-4.3 S ^
Processing-S]
Solver^ CFX_Build<Hl
CFX-4.3 ^ g
Pre-Processing^r
AEAT
^ Pre-Processing, Solver, Post-
- Fig. l-3
(staggered grid)*
: # ^ , Post-Processing^ CFX_Visualize^ £\f>}<^
CFX-4.3 2 E £ l ^ 2 : » -a^*>jl Si4- CFX-4.3
Rhie-Chow . CFX-4.3 3 E
CFX-4.3 3E«fl^fe
^ 2:?i-g- 71 # 1 - xifl
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KAERI/TR-1739/2001
1/4 S-ig-i l t } a , ] #
^ A 1/4
1/2
. o]
4
SDS2S1 ^ ^ ^ l ^ - o l l t f l ^ - 3|-£AOVE]] « | ]^^ . 3^>^ 1/4
^ ^ S ^ ^ * l e | ^ ^ SLtflSL 1.2 a?V ^-S- i
^ . ^ SIMPLE (Semi-Implicit Method for Pressure-Linked Equation)[18]2}- SIMPLEC
(SIMPLE Consistent) ^ J l ^ # [ 1 6 ] l : 7 ] ^ - ^ ^ A>-g-§>^^.^, ^S^-n f l ^ - ^ . ^ oflal?i)Xj.^.
PISO (Pressure- Implicit with Splitting of Operators) ^•JLS)#[19]4- ^>-§--5>^4. ^-S^u}-, PISO
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KAERI/TR-1739/2001
CALANORIACALANORIA SHELLCALANDRIA TUBESEMBEDMENT RINGFUELING TUBESHEETEND SHIELD LATTICE TUBESEND SHIELD COOLING PIPESINLET-OUTLET STRAINERSTEEL BALL SHIELDING
10 END FITTINGS11 FEEDER PIPES12 MODERATOR OUTLET13 MODERATOR INLET
14 FLUX MONITOR AND POISON INJECTION15 ION CHAMBER16 EARTHQUAKE RESTRAINT17 VAULT WALL18 VAULT COOLING PIPES19 MODERATOR OVERFLOW20 PRESSURE RELIEF PIPES21 PRESSURE RELIEF DISC22 REACTIVITY CONTROL ROD N0Z2LES23 VIEWING PORT24 SHUTOFF ROO25 ADJUSTER ROD26 CONTROL ABSORBER ROD27 ZONE CONTROL ROD28 VERTICAL FLUX MONITOR
Fig. 1-1 Reactor Assembly
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KAERI/TR-1739/2001
HELIUM VENT LINES
LIQUID liUECTION SHUTDOWN UNIT
HELIUM SUPM.Y TANK
POISON.MODERATOR IMTEBfACE
Fig. 1-2 Schematic of Liquid Injection Shutdown System
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KAERI/TR-1739/2001
GeomertryFile
CommandFile
UserFORTRAN
Dump File
Output File
Pre-Processing Solver Post-Precessing
Fig. 1-3 Structure of CFX-4.3 Code
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KAERI/TR-1739/2001
2.
71
Body-Fitted Gr id*
. CFX-4.3 S ^ ^ A ^
.3^- 3
Rhie-Chow
2.1
2.1.1
o
O
dt
djpuj)( 2" 2 )
fe stress tensor
> ^ Kronecker delta 0 ,4 .
dt
i'uj'^ Reynolds stress tensorH} §>^, R{j£. S.7]-s}x^} 4 # 4 go]
turbulent viscosity °]4-
(2-4)
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KAER1TR-1739/2001
O # € ^ VM^d(pYA) 3d
dt '
°*7W, YAr= # A$
coefficient)0] t\.
d(pYA) idt '
°^7l^:l, Sct^r turbulent
OUJYA) d I
dxj dXj \f
mass fraction °lt}\
§-oj] t)!S}c^ s l | ° ! ^
J(PUJYA) d
dxj dxj
Schmidt number
D 9YA )
UAB •<— ->T —i o -^i ^T -D
Y^DAB 1 5Cf j ^ j
Z).Bsl AQ
(2-5)
: (diffusion
(2-6)
•gr Perry's
2.1.2 \+^- S.1^ (Turbulent Models)
o
O
3^ 3z_f 9;
(2-1 OH -^rSt^: 52-1 o)|
(viscous sublayer)
(2-7)
(2-8)
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KAERLTR-1739/2001
2.2 o l#
2.2.1 Body-Fitted Grid
3 ftThompson, Warsi n e } ^ Mastin[25]^l - i - '<>]•%•$!:
)4 . Fig. 2-1^
. CFX-4.3 2 £ ^
Rhie-Chow
2.2.2
Fig. 2-1
# Fig.
(2-iD
JL, /fe- Jacobian ^ ^ - ^ .
J^X^IL _ ^x 22.
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KAERI/TR-1739/2001
N, S, E, W q
o] | [ ]o>^ -^. Jacobian ^ - t -
J
(2-17)^,
as4>s+
(2-19)^1 31^r aE, aw, aN, as %
aE= j +Max[-
+Max[(pG1Sv)w,0]
+Max[-
^ + Maxl
a w+ aN + as -
hybrid $•§• 4 - 8 - ^ : ^ ^
aE=Max[- {PGl8n).,£
9 ) y (
n,
{pGf7))e,0
(2-16)
(2-17)
(2-19)
scheme)
(2,20b)
(2-20c)
(2-20d)
(2-20e)
(2-21a)
(2-2lb)
(2-21c)
(2-21d)
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KAERI/TR-1739/2001
aP = aE+ aw+ aN+ as+(2-21e)
( P G28£)n - (p G2S$)S
2.3
2.3.1 Pressure-Velocity Coupling
Ale)
/ f W "T"
«
VP =
Bu = -i 8q87)ldp , Cu
=
(2-25)^
+CU drj (2-22a)
(2-23)
(2-24a)
t; = »* + [Bu-^ + C u ^ ) (2.24b)
| f - B * ) - f t (2.25b)
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KAERI/TR-1739/2001
G2= Gl + {CV% -
= 0
aPpP= awpw+ aNpN+ asps+ mp
2.3.2 Rhie-Chow
(2.26a)
(2-26b)
Chowfe \S$ ^ ^
(2-27)
(2-28)
(2-29)
<2-30>
(2-31)
(2-32a)
( 2 " 3 2 b )
(2-32d)
(2-32e)
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KAERI/TR-1739/2001
( 2 . 3 3 )
I a|) (2-35)
7}
^l(2-35)7> Rhie-Chowl overbarfe-
Rhie-Chow
2.3.3 SIMPLER SIMPLEC
SIMPLER SIMPLEC , Fig. 2-2Sf ^ 4 . p
- SIMPLER SIMPLEC^ ^}^1^
= Sanbunb' + {pp - pE)Ae
ue =- pB')Ae
ae- aZanhunb
7} S\3L, SIMPLER a=0, SIMPLEC - a =\±S.
^ m 1 H 0^ f i ^ - t * Dl^l^l ^fe4- Tcq-t t i s l f(relaxation factor)* SIMPLECS] ^ ^ - 7 f c) 3.711
L, u\v
(2-36)
(2-37)
. ^, SIMPLE^ SIMPLEC^
TO
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KAERI/TR-1739/2001
Table 2-1 Constants of Standard k- e Model
Launder & Spalding[22]
Sondak & Pletcher[23]
Demirdzic et al.[24]
CFX-4.2
Manual[16]
CM
0.09
0.09
0.09
1.44
1.44
1.44
1.92
1.92
1.92
Ok
1.0
1.0
1.0
1.3
1.22
1.217
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KAERFTR-1739/2001
NWo
Wo-
o
SW
No
o
s
NE
o
E
-o Js
o
SE
Fig. 2-1 Finite Difference Grid for Physical and Transformed
Computational Plane
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KAERI/TR-1739/2001
Update
P' = P
u = u
v' = v
V)' = V>
[ START ]
STEP 1: Solve discretized momentum equations
aeu,
a>u< =
'nb + (p'p- p'E)A,
STEP 2 : Solve pressure correction equation
aPpP=
STEP 3: Correct pressure and velocities
P= p' + p', u= a* + u , v = v' + v , w = w' + to
STEP 4 : Solve all other discretized transport equation
No
Fig. 2-2 SIMPLE Algorithm
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KAERFTR-1739/2001
3.
1/45.
3.1
1/2
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14
1/4.$j-§.,g.
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3367fl< fe Fig. 3-1 o]]
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1/4
3.717} 1/4S.
£1^4. ne]4-,
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KAERI/TR-1739/2001
g- Fig. ^ 3 . ±4
5° JL
7}
e^fe. i3x)*H
fe Fig.
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H CFXBuild ^ &
$££43- ^ 307fl ]fe 1/4USRSRC ^ t i .
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Table 3-2^1]
CFX-4.3 H f e Body-fitted gr id* 71-g-
^ M w, E,
§ 4 . Fig. 3-3
N,
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KAERiyTR-1739/2001
- Fig. 3-4
- Fig. 3-4(a)
6.25 Fig. 3-4(b)fe 3.125
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1-1% 6120
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Fig.
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KAERI/TR-1739/2001
£ : 1 m
H £ r 0.0 PaS.
1, 2, 5 g 107^ 47H
170X112, 170X224, 170X100, 170X170^1^. 170Xl00°ll tfl^ ^x> ^ - 2 : ^ Fig.
3.2.2
3.°]
[26]. Fig.
Fig. 3-7^: a . ^ , <$ x < 5d ^
x
WygnaskiSf Fiedler[27]fe ^ 40d<^-^ ^ # € 4 ^ ^-a«>^l^ . Fig. 3-7£-
, source-jetfi|- -^^1 #%•§• ^ - ^ ^ S-A>?t ^-f, real-jetofl
t t nef)5.4. source-jet^]
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Fig. 3-8^: ^ ^ ^ ^ £ ^ £ « M-Bl-^4. ^ £ ^ S ^ ^ £ ^ f e ^ 3 4^>^7> 27fl
5, 107US! ^^-fe i 7 ] a^ i - i s ^
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Fig. 3-9(a
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\£\ real-jet
source-jet 7f|'£];ol y£|3|'tt1?]r'€!' -M4"B" -*<!!<£3:'5:Kr7)-011 t^\^V
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KAERLTR-1739/2001
3.3.1 331S?1 ^ A A
£r A^^r 3*}^ ^<&A%- #*H SM, ^*<H1 ^ source-jet -real-jet efl#&£
20m/s 3. 3<^>7fi ^ J s ^ ^^ .S . - i W & 4 - AQ ^ ^ ^ Figfe Fig. 3-1H]
27fl ol^-o] 3.^.7]. Hf -§M, ^ ^ ^If-^ i^# *1»£ 3.2
6.25 mmS ^^^ l^^ l ^ # ^ ^ ^ 1 1 - 3.2 mm
4. ^^ t i o v *^ ^4fe 5°a AAQ y 1 5 ^ ^ 4 » ^ 1 A>-§-«> JflWa 3-3 1
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Fig. 3-12fe ^-a t # ^^S.^E^ i&^itHK^S. # ^ » Fig. 3-13^ r-x. Fig. 3-121- £& ^ £ ^ £ § ^^^r^Ai ^ ^^1§]-JL ^
HA-1 4 ^ ^-^>» a.oljl 814. Fig. 3->^S. 33571)51
r < 0.2m 5) ^ ^ H W ^tfl 1800 ppm %SL£\ ^ H »real-jet^ ^ A } jzfs}- cfl^]^ 0.3. <^^]s|-fe 7jo.s i-MlsM-. Fig. 3-15^- O.r-x sg^ofl tfl^ ^ £ ^-2-Ai (concentration contour)^: i+Bj-^14.
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3378
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KAERI/TR-1739/2001
5.SL SDS2S1
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KAERI/TR-1739/2001
Table 3-1 Comparison of Liquid Injection System and 1/4 Model
Unit
Injection
Pipe
Pitch
Hole
Calandria
Shell
Injection System[14]
Number
6
21
16
(per pitch)
1
Length
(mm)
6952
(per unit)
285.75
(per pitch)
•
5943.6
Diameter
(mm)
56
•
3.2
6756
(inner)
7594
(outer)
Quarter Model
Number
1
1
4*
(per pitch)
•
Length
(mm)
1428.5
285.75
(per pitch)
•
•
Diameter
(mm)
56
•
3.2
•
* Four holes are treated as sources and, therefore, there is no hole in the calculationmodel. Also, calandria shell is neglected in the model, and domain size isdetermined based on the radius of calandria shell.
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KAERI/TR-1739/2001
Table 3-2 Source Terms in Boundary Condition
sP
Sc
Velocity
— PVinlet
PVjnietVjn/et
Mass Flow Rate
0.0
pVinlet A ^fa
Mass Fraction
— PV inlet
PV Met 4> inlet
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KAERI/TR-1739/2001
Table 3-3 Structure and Number of Grid for Radial Direction
Number of Grid
(radial)
69
96
111
121
335
Grid Structure
Stretching
Stretching
Stretching
Stretching
Uniform
* The grid for axial direction is divided non-uniformly with total number of 59.
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KAERI/TR-1739/2001
y: 1/8" (3.2 mm) Dia. Hole
Wall thickness 0.10" (2.5 mm)
do"
Cross Sectionthrough Injection
2.20" (55.9 mm> W Nozzle (Full Size)
O O P t o o o o i
' o o o
(a) Injector
(b) Cross Section
Fig. 3-1 Injection Nozzle
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KAERI/TR-1739/2001
Fig. 3-2 Schematic Quarter Model of Injection System
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KAERI/TR-1739/2001
Fig. 3-3 Source in Arbitrary Mesh Center
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KAERI/TR-1739/2001
(a) Grid size (dx) = 6.25 mm
(b) Grid size (dx) = 3.125 mm
Fig. 3-4 Comparison of Velocity Vector for Real- and
Source-jet Calculation
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KAERI/TR-1739/2001
Pressure Boudary
mda
rylB
oiW
ai
(1) (2)
•
2.75 m
Calculation Domain
r Symmetric Line
i
S
• '
\
i
r
3IwoIis
40 m/sec( J is the velocity in the real condition and Qf the velocity as the source term.
Fig. 3-5 Calculation Domain of Free Jet
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KAERI/TR-1739/2001
Fig. 3-6 Grid Structure for Free Jet Calculation
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KAERLTR-1739/2001
0.8 -
0.6 -
1 0.4 -
0.2-
0.0 -
10 20 30
x/d
• Measurement
—+— Real-jet
Sourece-jet
40 50 60
Fig. 3-7 Comparison of Axial Velocity Profile for Real- and
Source-jet along Jet Direction
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KAERFTR-1739/2001
O
o
10 20 30
x/d
1.0-
0 .8 -
0.6-
0.4-
0.2-
0 .0-
\ \ \y.\v\
1 I ' 1 ' I • I
o Measured
—+—Real-jet
Source-jet
N = 1
[ N = 2N = 5
N = 10
' 1 *
—
40 50 60
Fig. 3-8 Comparison of Axial Concentration Distribution
for Real- and Source-Jet
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KAERI/TR-1739/2001
oooCD
a.
80-
60-
40-
20-
0-
Number of grid
N = 1
N = 2
N - 5
real-jet
— .
20
x/d
(a) Velocity
o
o
ooo
cO
100
80 -
4 0 -
10 20
x/d
/ X
Number of grid
N ~ 1
N = 2
N = 5
- real-jet
30 40
(b) Concentration
Fig. 3-9 Percent Error between Prediction and Experiment
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KAERLTR-1739/2001
pressure boundary
"OCOooCDEE
source—jet
285.75
ooo^CDEE
oinCOco
CO
centerline
Fig. 3-10 Two-Dimensional Domain for Real- and Source-jet Calculation
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JOJ 3jnjotuj§ pur) \\-£
9 0 Z'O * I-0I I I I 1 1 1 1 1 I 1
-I/O
-20
-eo'
- 9 0
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KAERI/TR-1739/2001
source-jet 69source-jet 121source-jet 335 (uniform)real-jet 69real-jet 121real-jet 335 (uniform
2.0E+I
O.OE+00,0.0
2.0E+01
0.0E-
0.5
Radial Distance (m)
(a) time = 0.1 sec
source-jet 69source-jet 121source-jet 335 (uniform)real-jet 69real-jet 121real-jet 335 (uniform)
0.5
Radial Distance (m)(b) time = 0.5 sec
Fig. 3-12 Comparison of Velocity for Real- and Source-jet in Radial Direction
(from hole of injection nozzle)
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KAERI/TR-1739/2001
real-jet source-jet
0.7r-
0.6-
0.5-
.0.4
0.3
0.2
0.1
0.7
0.6
0.5
0.4
0.1
0.1 0.2 0.3x(m) time = 0.1s
(a) time = 0.1 s
0.1 0.2 0.3x(m)
real-jet source-jet
0.7r-
0.6 -
0.5-
.0.4 2
0.3
0.2
_
— ' nllltl
' " " Ill[];;;;;;;;;;: m i
iiiiiii lpl
0.7r-
0.1
1 _
0.3
time = 0.7 s
(b) time = 0.7 s
0.1 0.2 0.3
x(m)
Fig. 3-13 Comparison of Velocity Vector for Real- and Source-jet
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KAERI/TR-1739/2001
source-jet 69source-jet 121source-jet 335 (uniform)real-jet 69real-jet 121real-jet 335 (uniform
O.0E+O0,
1.0E+04
1.0E
0.0E+00,
Radial Distance (m)
(a) time = 0.1 sec
0.5
Radial Distance (m)(b) time = 0.5 sec
Fig. 3-14 Comparison of Concentration Distribution for Real- and Source-jet
in Radial Direction (from hole of injection nozzle)
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KAERI/TR-1739/2001
0.7
0.6
0.5
0.4
0.3
0.2
0.1
real-jet
-
-
: 498.946
—
\ ]§?
0.7i-
0.6
0.5
0.4
0.3
0.2
0.1
source-jet
499.955
0.1X
0.2
(m)0.3
time = 0.1s
(a) time = 0.1 sec
0.1X
0.2(m)
0.3
0.7
0.6
0.5
0.4
0.3
0.2
0.1
real-jet
498.946
0.7i-
0.6
0.5
.0.4
0.3
0.2
0.1
I , ,
source-jet
499.955
i l . i
0.1
X
0.2
(m)0.3
time =
(b) time =
0.5 s
0.5 sec
0.1X
0.2(m)
0.3
Fig. 3-15 Comparison of Concentration Contour
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KAERI/ER-1739/2001
4.
3.2 mm7l-
^ 767fl
27171- #
. 51 ^ ^ ^
AECLS]
Fig. 1-2
4.1
Fig. 4-14
3378 mm 28
SDS2
7} AECL21 27.786
, e} 0.09 m3
^ ^ 0.08 m3 ^14- Fig.
- 52 -
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KAERI/TR-1739/2001
lfe Fig 1-15} 20«i Fig.ol
Fig. 4-1S]
1640.9 cm2 a]
48.1 cm ^ ^
^ a f e Fig.
, o]
y, z . r75/HS 4 - 3 ^ 199,875
(205X75X13)71)^ 1/4
Fig. 4 - 4 ^ 6 (a), (b)
5514
^-|-«1-Sa4.
^-^0=14. a 4-H1
fe 357B
7] $\ £-£:
41X75X45
8000 ppmSl
^ A ] ( 2 _ 7 )
51^112
4.2
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KAERI/TR-1739/2001
4.2.1 - f r * ^ 5L&
Br r-x ^ ^ 3 M 4 4 ^ 3 . $14. Fig. 4-5fe ^ ^ ^ # 0 ] ^ W r-x
. Fig. 4-6fe <4 4 1 ^ ^ 4 . Fig. 4-6(a)#
°fl 4 4Fig. 4-5S] ^|E.fi] z3o}7} ^ ^ ^ °1 ] 4 4
4 "3"^ 4 f e A}^o]^, olfe Fig. 4-6(b)
3.2
Fig.
Fig. 4-7£ \+^- £<H] tfltt -tJLAj(contour)o|51, F i g .
4 4 ^-^*1 ^ 0 ^ 4 . Fig. 4-8(a)» S.^ /-l^o] xl -ofl 4 4
- 44 #
4.2.2
. 2-7]
4 4 71%Jl
4 ^Tfl ol^<^^)4 Al^ol d x l4^ o]^ Sl HlAi ^ ^ ^ j | i 4 f tg^-^4 Fig. 4-10fe
44
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KAERI/TR-1739/2001
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KAERI/TR-1739/2001
Table 4-1 Boundary Condition and Physical Properties
Boundary Conditions
Injection
Velocity
Concentration of
Injection Poison
Outlet Condition
27.786 m/s
8000 ppm
Pressure
Boundary
Physical Properties
Density of
Moderator
Density of
Poison
Viscosity of
Moderator
Diffusion
Coefficient
1098 kg/m!
1127 kg/mJ
8.5E-04
(kg/m • s)
5.68E-07
(kg/m • s)
Model Condition
Mesh
Pressure Reference Point
Algorithm
41X75X45
22,75,23 (ij,k)
(Outlet Center)
SIMPLEC
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KAERI/TR-1739/2001
Outlet (Pressure Boundary)
Fig. 4-1 Schematic Diagram of 1/4 One-Pitch Model
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KAERFTR-1739/2001
(a) x-6 Plane
(b) r-x Plane (c) x- 6 Plane (side)
(d) x-8 Plane (top)
Fig. 4-2 Grid Structure for 1/4 One-Pitch Model
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KAERLTR-1739/2001
1.5
0.5
-0.25 0 0.25
x(m)
(a) Time = 0.1 sec
1.5
6 1
0.5
-0.25 0 0.25
x(m)
(b) Time = 0.3 sec
1.5!
0.5;
-n.25 0 n.25
x(m) •
(c) Time =0.7 sec
1.5
0.5
-0.25 0 0.25
x(m)(d) Time =1.1 sec
Fig. 4-3 Velocity Vector for Five-Pitch Model in r-x Plane (K = 7)
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KAERI/TR-1739/2001
\
(a) grid number = 1 3 ( 5 direction)
(b) grid number = 35 ( 9 direction)
(c) grid number = 45 ( 9 direction)
Fig. 4-4 Streamlines of r- 9 Plane (time = 0.7 s)
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KAERI/TR-1739/2001
1.2
0.8
0.4
JL
1.2
0.8
0 0.2
x(m)(a) t ime^ 0.1 s
0.4
0 0.2
x(m)(b) time = 0.3 s
1.2rr 1.2rr
0.4 » 0.4 •
(c) time = 0.7 s (d)time= 1.0 s
Fig. 4-5 Velocity Vector by Poison Injection in r-x Plane (K = 23)
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KAERI/TR-1739/2001
a)OH
1.5E+03
l.OE+03 Ht
5.0E+02
O.OE+00
-5.0E+02
-1.0E+03
-1.5E+O3
2.0E+03
1.0E+03 h
O.OE+00 F
-1.0E+03 h
-2.0E+03
x(m)
(a) Radial Direction
-
—
\ \VI\\
&ftI ^ >i \'ji
h 4i\V'j
! ij ii 1 i
/
1k
- - — -ime = O. I sime = 0.3sime = 0.5sime= 1.0 s
r= 0.5371 m
itiii
'ii
r= 0.028954 m1 >
/
/
1-0.1 0
x(m)
(b) Axial Direction
0.1
Fig. 4-6 Pressure Distribution
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KAERI/TR-1739/2001
1.2
0.8
0.4
1.4875
j _
1.2
0.8
0.4
' 1.48827
Z96654
'7M13
1.2
0.8
0.4
1.4875
14.44429
7.4017.40108
1.2
0.8
0.4
0 0.2 " 0 0.2x (m) x (m)
(a) time = 0.1 s (b) time = 0.3 s
0 0.2x(m)
(c) time = 0.5 s
i '0 0.2x(m)
(d) time = 1.0 s
Fig. 4-7 Turbulent Viscosity Contour in r-x Plane (K = 23)
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KAERI/TR-1739/2001
20
15
10 -
5 -
I
20
15
10
-
- \
• K
•
\ ^ 1 ,
_ _ _ _
"\_
\\
time = 0.1 stime = 0.3 stime = 0.5 stime= 1.0 s
\\
\\
0.5r(m)
(a) Radial Direction
1.5
time = 0.1s— — — time = 0.3 s
time = 0.5 stime= 1.0s
-0.1 0.1
(b) Axial Direction
Fig. 4-8 Turbulent Viscosity
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KAERI/TR-1739/2001
1.2rr
0.8
0.4 499.981
1.2rr
0.8
0.4
J L
499.981
J _0 0.2 0 0.2
x (m) x (m)(a) time = 0.1 s (b) time = 0.3 s
1.2
0.8
0.4
499.981
999.963
1499.94
A1499.94III \\\1999,93
_L
1.2
0.8
0.4
0 0.2
x(m)(c) time = 0.5 s
0
499.981
999.963
499.94
999.9
Mj _0 0.2
x(m)(d) time = 1.0 s
Fig. 4-9 Concentration Contour in r-x Plane (K = 23)
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KAERI/TR-1739/2001
ao
§oO
2.5E+03
2. OE+03
1.5E+03
1. OE+03
5.0E+02
O.OE+00
time = 0.1 stime = 0.3 stime = 0.5 stime= 1.0 s
r(m)
Fig. 4-10 Concentration Distribution in Radial Direction
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KAERFTR-1739/2001
5. ^
DUPIC CANDU
CFX-4.3 3 £
^ 1/4
2)
3)
±§•5. (reactor physics) «>-§-
SDS251
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KAERI/TR-1739/2001
6.
SDS2<>11fe Fig. l-2ofl
2)
3)
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KAERI/TR-1739/2001
, 1999, " 3 ^ 3 . <S31 «|«?!3*M 7 | ^ 7 f l ^ - DUPIC
KAERI/RR-1999/99.
2. J.S. Lee, K.C. Song, M.S. Yang, K.S. Chun, B.W. Rhee, J.S. Hong, H.S. Park, C.S. Rim, H. Keil,
1993, "Research and Development Program of KAERI for DUPIC (Direct Use of Spent PWR Fuel
in CANDU Reactors)", Proceedings of International conference and Technology Exhibition on Future
Nuclear System: Emerging Fuel Cycles and Waste Disposal Options, GLOBAL'93, Seattle, pp.
733-739.
3. « H ^ § ^ k 1996, " ^ 2,3,43L7} $f^#^£^iLjL-H", 4 6.5=£.
4. S. Nawathe, M.K. Sapra, L.R. Mohan, M.K. Nema and S.C. Mahajan, 1997, "Development and
Qualification of Liquid Poison Injection System (SDS-2) for 500 MW(e) PHWRs", Presented in
Work shop on Reactor Shutdown System, IGCAR, Kalpakkam, pp. IV.4.1-IV.4.11.
5. H. Tennekes and J.L. Lumley, 1972, "A first Coourse in Turbulence", The MIT Press.
6. J.O. Hinze, 1975, "Turbulence", McGraw-Hill.
7. P.M. Sforza, M.H. Steiger, and N. Trentacoste, 1966, "Studies on Three-Dimensional Viscous Jets",
A.I.A.A. J. 4, pp. 800-806.
8. W. Rodi and D.B. Spalding, 1970, "A Two-Parameter Model of Turbulence, and its Application
to Free Jets", Warme und Stoffubertragung, B.3, pp. 85-95.
9. % ^ ^ , 1998, "
10. J.O. Hinze and B.G. Van Der Hegge Jijnen, 1949, "Transfer of Heat and Matter in the Turbulent
Mixing Zone of an Axially Symmetrical Jet", Appl. Sci. Res. Al., pp. 435-461.
11. D.B. Spalding, 1971, "Concentration Fluctuations in a Round Turbulent Free Jet", Chemical
Engineering Science, 26, pp. 95-107.
12. C.S. Walker, 1966, "Secondary shutdown system of nuclear power plants", ORNL, ORNL-NSIC-7.
13. A.R. Dastur, 1977, "Confirmation of CANDU shutdown system design and performance during
commissioning", AECL, AECL-5914.
14. AECL, 1996, "Design Manual Liquid Injection Shutdown Units", Revision 6, XX-31760-DM -000.
15. # » g ^ , 1995, " € ^ 2,3,45171 42 ^^7flf-(SDS2) i = 2 = $ M ^ ^ ^ ^ W 2L5L
*\", 1993.03.01-1995.02.28, Canada, tR--&*r^ Q^^i, KAERI/OT-132/95.
16. AEA Technology, 1997, "CFX-4.2 Manual."
17. CM. Rhie, W.L.Chow, 1983, "Numerical Study of the Turbulent Flow Past an Airfoil with Training
Edge Separation", AIAA J. 21, pp. 1525-1532.
18. S.V. Patankar, 1980, "Numerical Heat Transfer and Fluid Flow", Hemisphere
19. R.I. Issa, 1985, "Solution of the Implicitly Discretised Fluid Flow Equations by Operator- Splitting",
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KAERFTR-1739/2001
J. Comp. Phys. 61, pp. 40-65.
20. S.W. Kim, T.J. Benson, 1992, "Comparison of the SMAC, PISO and Iterative Time-Advacing Schemes
for Unsteady Flows", Comput. Fluids, 21, pp. 435-454.
21. R.H. Perry, D.W. Green, J.O. Maloney, 1984, "Perry's Chemical Engineers' Handbook", 6th edition,
McGraw-Hill, pp. 3.286-3.287.
22. B.E. Launder, D.B. Spalding, 1974, "The Numerical Computation of Turbulent Flows", Comput.
methods appl. mech. eng., 3, pp. 269-289.
23. D.L. Sondak, R.H. Pletcher, 1993, "Application of Wall Functions to Generalized Nonorthogonal
Curvilinear Coordinates Systems", AIAA 24th Fluid Dynamics Conference, July 6-9, AIAA 93-3107,
pp. 1-19.
24. I. Demirdzic, A.D. Gosman, R.I. Issa, M. Peric, 1987, "A Calculation Procedure for Turbulent Flow
in Complex Geometries", Comput. Fluids, 15, pp. 251-273.
25. J.F. Thompson, Z.U.A. Wasi, C.W. Mastin, 1982, "Numerical Grid Generation", North-Holland.
26. J.A. Schetz, 1980, "Injection and Mixing in Turbulent Flow", AIAA, 68, Chapter II.
27. I. Wygnanski and H. Fiedler, 1969, "Some Measurements in the Self-Prserving Jet", J. Fluid Mech.
38, pp. 577-612.
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KAERI/TR-1739/2001
APPENDIX
A.1 CFX-4.3 COMMAND FILE
£-§- CFX-4.3 3.B.Z] COMMAND FILEtfl«V
A]-g--sT: real-jet a.A}c>lj7, ^ g*ty ^ ^ " S ^ - 3x>^ 5s|*l 1/4
»MODEL TOPOLOGY^ Tfcb ^ ^ * ^ ^ ^ ^ 4 ^ S f 4 ^.^.ofl cfl^ PATCH* ^>#<H 1+
f"=fl »MODEL BOUNDARY CONDITIONS'^ ^^I?J:-i- # ^r SlH^- 5 ] ^ $14. °1 S€ r
^w.^-Bi^: »CFX4<?]:i $ 1 4 4 i ^ S »MODEL D A T A ^ A ^ X}^- 7 l ^ , -fj- 1 ^J-Efl^^
7l^*V4. -n- 1 Aov^l^^ »PHYSICAL PROPERTIES^ ^w.f -H »FLUID PARAMETERS^A1 € ^ « H , CFX-4.3^)]^ ^ l € « f e PCP t lHEi l - o]^-^- ^ 014.
0 ] ^ . && »TURBULENT PARAMETERS'3] t\ ^
Prandlt ^ ^ ^ * N t f l ^ w ^ A } ^ 41-^^1-^ - ^ ^ ^ ^ ^
j ^ f ] ^ ^ ^ ) ^ ^ ^ a i e l # , o ] ^ 31^&, »MODEL
»OUTPUT OPTIONS^
COMMAND FILE 1
»CFX4
» S E T LIMITS
TOTAL INTEGER WORK SPACE 3500000
TOTAL CHARACTER WORK SPACE 5000
TOTAL REAL WORK SPACE 10000000
»OPTIONS
TWO DIMENSIONS
BODY FITTED GRID
CYLINDRICAL COORDINATES
AXIS INCLUDED
TURBULENT FLOW
ISOTHERMAL FLOW
INCOMPRESSIBLE FLOW
TRANSIENT FLOW
MASS FRACTION EQUATIONS 1
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KAERFTR-1739/2001
»MODEL TOPOLOGY
»CREATE BLOCK
BLOCK NAME 'BLOCK-NUMBER-1'
BLOCK DIMENSIONS 59 318 1
»CREATE PATCH
PATCH NAME 'PRESS'
BLOCK NAME 'BLOCK-NUMBER-1'
PATCH TYPE 'PRESSURE BOUNDARY
HIGH J
»CREATE PATCH
PATCH NAME 'SYMMETLEFT
BLOCK NAME 'BLOCK-NUMBER-1'
PATCH TYPE 'SYMMETRY PLANE1
LOW I
»CREATE PATCH
PATCH NAME 'SYMMETRIGHT
BLOCK NAME 'BLOCK-NUMBER-1'
PATCH TYPE 'SYMMETRY PLANE'
HIGH I
»CREATE PATCH
PATCH NAME 'HOLE1'
BLOCK NAME 'BLOCK-NUMBER-1'
PATCH TYPE 'INLET
PATCH LOCATION 21 21 1 1 1 1
LOW J
»MODEL DATA
»AMBIENT VARIABLES
U VELOCITY 0.0000E+O0
V VELOCITY 0.O000E+OO
PRESSURE 0.0000E+00
K 1.0000E-04
EPSILON 1.0000E-04
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KAERI/TR-1739/2001
MASS FRACTI0N1 0.0000E+O0
»DIFFERENCING SCHEME
ALL EQUATIONS 'HYBRID'
» S E T INITIAL GUESS
» S E T CONSTANT GUESS
U VELOCITY 0.0000E+00
V VELOCITY 0.O000E+OO
PRESSURE O.OOOOE+00
K 1.0000E-04
EPSILON 1.0000E-04
. MASS FRACTION1 O.OOOOE+00
»PHYSICAL PROPERTIES
»FLUID PARAMETERS
VISCOSITY 8.5000E-04
DENSITY 1.0980E+03
» M A S S TRANSFER PARAMETERS
»DIFFUSIVITIES
MASS FRACTION1 5.6800E-07
»TRANSIENT PARAMETERS
»FIXED TIME STEPPING
TIME STEPS 12* 1.000000E-01
INITIAL TIME 0.0000E+00
»TURBULENCE PARAMETERS
»TURBULENCE MODEL
TURBULENCE MODEL 'K-EPSILON
»TURBULENCE CONSTANTS
CMU 9.0000E-02
Cl 1.4400E+00
C2 1.9200E+00
C3 O.OOOOE+00
CAPPA 4.1870E-01
»TURBULENT PRANDTL NUMBER
K 1.0000E+00
EPSILON 1.2170E+00
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KAERI/TR-1739/2001
MASS FRACTION1 9.0000E-01
»LOGLAYER CONSTANT
VELOCITY 9.793 OE+00
MASS FRACTION1 9.7930E+00
»SUBLAYER TfflCKNESS
VELOCITY 1.1225E+01
MASS FRACTION1 1.1225E+01
»SOLVER DATA
»PROGRAM CONTROL
MAXIMUM NUMBER OF ITERATIONS 9999
PRESSURE REFERENCE POINT 30 318 1
MASS SOURCE TOLERANCE 1.0000E-06
TRACE MAXIMUM RESIDUALS
»PRESSURE CORRECTION
SIMPLEC
»TRANSIENT CONTROL
»CONVERGENCE TESTING ON VARIABLE
PRESSURE
»UNDER RELAXATION FACTORS
U VELOCITY 6.5000E-01
V VELOCITY 6.5000E-01
PRESSURE 1.0000E-01
VISCOSITY 7.0000E-01
K 7.0000E-01
EPSILON 7.0000E-01
MASS FRACTION1 1.0000E-01
»CREATE GRID
»SIMPLE GRID
BLOCK NAME 'BLOCK-NUMBER-1'
DX 20* 4.682500E-03 3.200000E-03 5* +
5.710000E-03 3.200000E-03 5* 5.710000E-03 +
3.200000E-03 5* 5.710000E-03 +
3.200000E-03 20* 4.682500E-03
DY .001012 .001023 .001035 .001047 .001060 +
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KAERFTR-1739/2001
.001072 .001085 .001097 .001110 .001123 +
.001136 .001149 .001163 .001176 .001190 +
.034349 .034749 .035155 .035565 .035980 +
.036399 .036824 .037253 .037688 .038127 +
.038572 .039022 .039477
DZ 1.000000E+00
X START O.0000E+OO
Y START 2.8000E-02
Z START -5.0000E-01
»MODEL BOUNDARY CONDITIONS
»INLET BOUNDARIES
PATCH NAME 'HOLE1'
NORMAL VELOCITY 2.0000E+01
TURBULENCE INTENSITY 5.0000E-02
DISSIPATION LENGTH SCALE 3.2000E-03
MASS FRACTION 1 8.0000E-03
»PRESSURE BOUNDARIES
PATCH NAME 'PRESS'
PRESSURE 0.0000E+O0
STATIC PRESSURE SPECIFIED
MASS FRACTION 1 0.O000E+O0
» S T O P
COMMAND FDLE 2
» C F X 4
»OPTIONS
THREE DIMENSIONS
BODY FITTED GRID
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KAERI/TR-1739/2001
CYLINDRICAL COORDINATES
TURBULENT FLOW
ISOTHERMAL FLOW
INCOMPRESSIBLE FLOW
TRANSIENT FLOW
MASS FRACTION EQUATIONS 1
» U S E R FORTRAN
USRSRC
USRTRN
»MODEL TOPOLOGY
»CREATE PATCH
PATCH NAME 'OUTLET
BLOCK NAME 'BLOCK-NUMBER-1'
PATCH TYPE 'MASS FLOW BOUNDARY
PATCH LOCATION 75 131 75 75 7 7
HIGH J
»MODEL DATA
»AMBIENT VARIABLES
U VELOCITY 0.0000E+00
V VELOCITY O.O00OE+O0
W VELOCITY O.000OE+00
PRESSURE O.0000E+O0
K 1.0000E-04
EPSILON 1.0000E-04
MASS FRACTION 1 O.0000E+O0
»DIFFERENCING SCHEME
ALL EQUATIONS 'HYBRID'
» S E T INITIAL GUESS
» S E T CONSTANT GUESS
U VELOCITY 0.0000E+00
V VELOCITY 0.0000E+00
W VELOCITY 0.0000E+00
PRESSURE O.000OE+O0
K 1.0000E-04
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KAERI/TR-1739/2001
EPSILON 1.0000E-04
MASS FRACTI0N1 O.000OE+O0
» W A L L TREATMENTS
WALL PROFILE 'LOGARITHMIC
NO SLIP
»PHYSICAL PROPERTIES
»FLUID PARAMETERS
VISCOSITY 8.5000E-04
DENSITY 1.0980E+03
»MASS TRANSFER PARAMETERS
»DIFFUSIVITIES
MASS FRACTION1 5.6800E-07
»TRANSIENT PARAMETERS
»FIXED TIME STEPPING
TIME STEPS 12*0.1
INITIAL TIME 0.0000E+00
»TURBULENCE PARAMETERS
»TURBULENCE MODEL
TURBULENCE MODEL 'K-EPSILON'
»TURBULENCE CONSTANTS
CMU 9.0000E-02
Cl 1.4400E+00
C2 1.9200E+00
C3 0.0000E+O0
CAPPA 4.1870E-01
»TURBULENT PRANDTL NUMBER
K 1.0000E+00
EPSILON 1.21700E+00
MASS FRACTION1 9.0000E-01
»LOGLAYER CONSTANT
VELOCITY 9.7930E+00
MASS FRACTION 1 9.7930E+00
»SUBLAYER THICKNESS
VELOCITY 1.1225E+01
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KAERI/TR-1739/2001
MASS FRACTI0N1 1.1225E+01
»SOLVER DATA
»PROGRAM CONTROL
MAXIMUM NUMBER OF ITERATIONS 5000
PRESSURE REFERENCE POINT 103 75 7
MASS SOURCE TOLERANCE 1.0000E-06
TRACE MAXIMUM RESIDUALS
»PRESSURE CORRECTION
SIMPLEC
»TRANSIENT CONTROL
»CONVERGENCE TESTING ON VARIABLE
PRESSURE
»CONTROL PARAMETERS
MINIMUM RESIDUAL VALUE O.OOOOE+00
MAXIMUM RESIDUAL VALUE 1.0000E+20
REDUCTION FACTOR 1.0000E+03
DIVERGENCE RATIO 1.0000E+05
»UNDER RELAXATION FACTORS
U VELOCITY 6.5000E-01
V VELOCITY 6.5000E-01
W VELOCITY 6.5000E-01
PRESSURE 1.0000E+00
VISCOSITY 6.0000E-01
K 7.0000E-01
EPSILON 7.0000E-01
MASS FRACTION1 1.0000E+00
»MODEL BOUNDARY CONDITIONS
»PRESSURE BOUNDARIES
PATCH NAME 'OUTLET
PRESSURE 0.0000E+O0
STATIC PRESSURE SPECIFIED
»OUTPUT OPTIONS
»PRINT OPTIONS
» W H A T
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KAERI/TR-1739/2001
U VELOCITY
V VELOCITY
W VELOCITY
PRESSURE
DENSITY
VISCOSITY
K
EPSILON
MASS FRACTION 1
»WHERE
K PLANES 7
»WHEN
FINAL SOLUTION
EACH TIME STEP
» S T O P
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KAERFTR-1739/2001
A.2 CFX-4.3 GEOMETRY FILE
1/4
fe $^}l:-€r patch o]f-4 n patch?}
vertices ] tfl^ ^ i # 4 1 ^ tflS}o ^^ t f l s 4 4 ^ 4
GEOMETRY FILE (1/4 five-pitch model)
/* GEOMETRY FILE FOR CFX-4 FROM CFX-MESFflMPORT */
1 5 0 199875 219184 /*
hffiLC€K,NPATCH,NGLUE,NELEHNPOINT */
/* BLOCK NAMES AND SIZE (NI,NJ,NK) */
BLOCK-NUMBER-1 205 75 13
/* PATCH TYPE, NAME, NO., RANGE, DIREC, BLK. NO., AND LABEL */
SYMMET SYMMET_DOWN 1
1 1 1 75 1 13 4 1 1
SYMMET SYMMETJLEFT 2
1 205 1 75 1 1 6 1 1
SYMMET SYMMET_RIGHT 3
1 205 1 75 13 13 3 1 1
SYMMET SYMMETJUP 4
205 205 1 75 1 13 1 1 1
WALL WALL_PIPE 5
1 205 1 1 1 13 5 1 1
/* BLOCK TO BLOCK GLUEING INFORMATION */
I* VERTEX CO-ORDS (X,Y,Z) FOR BLOCK 1 •/
-0.714375E+00 0.280000E-01 0.785398E+00
-0.702619E+00 0.280000E-01 0.785398E+00
-0.691651E+00 0.280000E-01 0.785398E+00
-0.681417E+00 0.280000E-01 0.785398E+00
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KAERFTR-1739/2001
A.3 CFX-4.3 USER FORTRAN (USRRSC)
•i- W - A £*r4) tfltt -£^£ ^ W - ^ I t e SP(INODE, IPHS)4 SUGP, IPHS)
flfe address ^ 5 1 ^ 4 . INODEfe
(phase) a iJ lS .^] 1-& liquid, 2fe gas, 3fe soHd
'PRESSURE' yo>;§^)l- ° l-8-«H SP = 0.0, SU =
3-241
USER FORTRAN (USRSRC)
SUBROUTINE USRSRC(IEQN,ICALL,CNAME,CALIAS,AM,SP,SU,CONV
+ ,U,V,W,P,VFRAC,DEN,VIS,TE,ED,RS,T,H,RF,SCAL
+ ,XP,YP,ZP,VOL,AREA,VPOR,ARPOR,WFACT)IPT
+ ,IBLK,IPVERT,IPNODN,IPFACN,IPNODF,IPNODB,IPFACB
+ ,WORK,IWORK,CWORK)
C
IF(CALIAS.EQ.'PRESSURE') THEN
C
CALL IPREC('BLOCK-NUMBER-1 ','BLOCK','CENTRES',IPT,ILEN,JLEN,KLEN,
+ CWORKJWORK)
C
DO I = 1,IMAXI
DO J = UJMAXJ
IIX = 12+41*a-l)+6*(J-l)
IUSRIP = IPaiX,IIY,IIZ)
SU(IUSRIP,1) = SU(IUSRIP,1) + GDM
END DO
END DO
END IF
C
IF(ICALL.EQ.2) THEN
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KAERI/TR-1739/2001
ENDIF
C
ENDIF
RETURN
END
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KAERI/TR-1739/2001
7)
INIS
KAERI/TR-1739/2001
(DUPIC
(DUPIC
2001. 1.
O] 82 p. S. 3. 7) 26 cm.
o ),( )
CANDU
1/4
nfl-f. CANDU
fe 27.8 m/s fe 8000 ppmr-x r- d
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KAERLTR-1739/2001
BIBLIOGRAPHIC INFORMATION SHEET
Performing Org.
Report No.
Sponsoring Org.
Report No.Standard Report No. INIS Subject Code
KAERI/TR-1739/2001
Title/Subtitle Jet Flow Analysis of Liquid Poison Injection in a CANDU Reactor Using Source Term
Main Author Chae, Kyung Myung (Choongnam University)
CoauthorChoi, Hangbok (DUPIC Fuel Compatibility Assessment)
Rhee, Bo Wook (DUPIC Fuel Compatibility Assessment)
Publication
PlaceTaejon Publisher KAERI
Publication
Date2001. 1.
Page 82 p. 111. & Tab. Yes ( V ), No ( ) Size 26 cm.
Note
ClassifiedOpen( V ), Restricted( ),
Class Document, Internal Use Only( )Report Type Technical Report
Sponsoring Org. Contract No.
Abstract (15-20 Lines)
For the performance analysis of Canadian deuterium uranium (CANDU) reactor shutdown system number 2(SDS2), a computational fluid dynamics model of poison jet flow has been developed to estimate the flowfield and poison concentration formed inside the CANDU reactor calandria. As the ratio of calandria shellradius over injection nozzle hole diameter is so large (1055), it is impractical to develop a full-size modelencompassing the whole calandria shell. In order to reduce the model to a manageable size, a quarter of one-pitchlength segment of the shell was modeled using symmetric nature of the jet; and the injected jet was treatedas a source term to avoid the modeling difficulty caused by the big difference of the hole sizes. For the analysisof an actual CANDU-6 SDS2 poison injection, the grid structure was determined based on the results oftwo-dimensional real- and source-jet simulations. The maximum injection velocity of the liquid poison is 27.8m/s and the mass fraction of the poison is 8000 ppm (mg/kg). The simulation results have shown well-establishedjet flow field. In general, the jet develops narrowly at first but stretches rapidly. Then, the flow recirculatesa little in r-x plane, while it recirculates largely in r- 6 plane. As the time goes on, the adjacent jets contacteach other and form a wavy front such that the whole jet develops in a plate form. This study has shownthat the source term model can be effectively used for the analysis of the poison injection and the simulationresult of the CANDU reactor is consistent with the model currently being used for the safety analysis. Inthe future, it is strongly recommended to analyze the transient (from helium tank to injection nozzle hole)of the poison injection by applying Bernoulli equation with real boundary conditions.
Subject Keywords(About 10 words)
CANDU, SDS2, Jet Flow, Liquid Poison Injection