NASA Technical Reports Server (NTRS) 19930017768: NTP system simulation and detailed nuclear engine modeling

28 Pages·0.66 MB·English

by  NASA Technical Reports Server (NTRS)

N93 - 2G 9
NTP SYSTFM giM! IIATION AND
DEi'AILED NU(..:I,F,AIt ENGINI". MOI)I'3,1NG
gamim Anghaie
Innovative Nuclear Space Power and Propulsion Institute
Universily of Florida
Presemed at
Nuclear Propulsion Technical Interchange Meeting
(NP-TIM-92)
October 20-23, 1992
NASA I_ewis Research Center
Plum Brc_)k Station
INHPI
Univcrs.ily ol" F]olida
NTP SYSTEM SIMULATION &
DETAILED NUCLEAR ENGINE MODEI,ING
Samim Anghaie
Innovative Nuclear Space Power & Propulsion Institute
University of Florida
Gainesville, FL
With Technical Contribution from:
Gary Chen, University of Florida
Jeff Given, University of Florida
James White, University of Florida
Steven Peery, Pratt & Whitney
Harold Garrish, NASA-MSFC
James Walton, NASA-LeRC
i
NTP:Systems Modeling 638 NP-TIM-92
i
INSi'[
Ihfivel _hy nf Fin,lda
MODELING AND ENGINEERING SIMULATION OF
NUCLEAR THERMAl+ ROCKET SYSTEMS
Modular Thermal Fluid Solver with Neutronic Feedback
Main Component Modules:
pip_s,Valves,Mixer
NozzleSkirt
Pump,Turbine
ReflectRoera,ctoCrore
Hydrogen (Para- attd Dissocialed) Property Package
10 ST _ 10,000 K
.1SP<160bar
Models Developed for N'IX-R, NERVA and XNR 2000
CFD and Heat Transfer Models for Main NTR Components
Adetailedprogramformodelingoffullsystemnuclearrocket enginesisdeveloped. At
present time, the modelfeaturesthe expandercycle. Axialpower dislHbutionin the
reactorcore is calculatedusing 2- and 3-D neutronicscomputer codes, Acomplete
hydrogenpropertymodelisdevelopedandimplemented.Threenuclearrocketsystemsare
analyzed. Thesesystemsare:a75,000IbfNERVAclassengine,a25,000lbfcermetfueled
engineand[NSPI'snuclearthermal vaporrocket.
INSPI
UniversityofFlorida
NUCLEAR THERMAL ROCKET SIMULATION SYSTEM
_-:_/--- .....
t77 I-
I_R$1"S03
_s2____.__.L__':y_.".o.....eI
[ "IC_D"HA_lR_£lr_r"trcLLgz"C*CTToORR l
-7....°....... 1
IIIt_L_r_i:6 "r_g_¢o0 yI,_.HIC
Sll'lG[,g STA_a H_[.A_-I,IKg A,P_.,¥SIS
STAll _O'J_-Lllfl[ _¢AF.YIIS
I_*O_CYLTg_ • vU__oq_ITR-YTYHIPI_.O.'.C,Mg.E?_OCKg'rtI
_[_RV& 10_RIV_gTIV_ _l.OCg[:l'
-- ho,_ 7
Thenminprogram links allthecon_ponenl modulesand ileralesto arriveat theuser
specifiedthrust chamberpressurea,_dlemp_ralmeandthisls[level. Reactorpowerand
propellant flowrateare amongoutputs of thesimulationprngram. FuelPleloenlsinthe
coremoduleareprismaticwithvariableflowarearmio. Eachmoduledividestherelative
NP-l_M-92 componenitntoNse_cnents.
639 N'n,:Sy,=teo_ Mod¢liag
i
iNSP[
UniversilyorFio_da
INSPI-NTVR Core Axial Flow Profile
Tc = 2750K Pc = 750psi F=750001bf
_{1000 ---
J
0_ • "
0 0.2 0.4 0.6 0.8 1
Normalized Length
Axial lemperature distribution of'_ fuel surface and propeJl_n! Jnan avera,_e power
rod. Reactor power isadjusted to achieve the tltrust chamt)er temperature and presstue
of 2750 Kand 750 psi, respectively.
[NSP[
UnJverslry o[ RoHda
INSPI-NTVR Core Axial Flow Profile
Tc = 2750K Pc =750psi F=750001bf
1.6
1.5
t.4
R
13
!
1.2
1.1
I
{).9
0 0.2 0.4 0.6 0.8
Norm,e!!zed Lellglh
Non'_lized axial powcr d|slHhulion in C-C composite fuel motr[x NTVR. c,lculRled hy
DOT-2 $,, code. The nJdalpower shape I',etor isan |np-t for the simulalion code.
NTP: Systems Modeling _) NP-TIM-92
INSPI
tJnlvetrhy of FL fid,_
Specific Impulse vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
1,OOO
980
960 ....... !..... ;........ !....... '......... _!1lC..h.a.m..b.er3oTe0m0p.K
i i '. ' ;_ * 2750K
940 ............................... :......... i/ ' 2500K
Q.
920
9OO
68O
I
860
600 700 ooo tmo 1,ooo 1,1on 1,2oo
Chamber Pressure (psi)
i
Parame(Hc study of thrusl chaml_r pr_sure and tentp_rature impact onlsp ofNI'VR. At
higher pressures [sp is less sensitive to thrust chamber temperalure,
INSPI
th+ivet_ily of Fl,,lida
Turbine Pressure Ratio vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
1+26
1.24
: : /.vr+ _
i .,+.z i / 1
1,22
1.2
1.18
2,_" i _ ilCh,m_rTemp.
1.16
1.14 ......._..+_.: ........ :........ :....... : : - v--- 2500K
h
1,12 .... i .... i .... i .... + , , , i ....
600 700 000 g00 1,00O 1,100 1,200
Chamber Pressure (psi)
Ita_.¢t
Turbine pressure ratio isserL_iciveto both thrus! chamber pressure and lemperature, For
thrust chamber pressure of"i200 psiand temperature of3000 K,the turbine pressure ratio
of 1,26 iswell wilhin the range of+available technology.
NP-TIM-92 64] NTP: Sy=le.ms Modeling
IN_I'I
tl.iv,'l_ity c_!ll,,li,l:s
NERVA Core Axial Flow Prolile
Tc = 2750K Pc = 750psi F=750001bf
3,500
i i .....*i'°" _..........
3,000
2,500
:_ 2,000
I 1,500
1,(X_O
illillllllil
500
0.2 o.4 O.S O.S 1
Normalized Length
/_dal leml_rmture profiles forNERVA-75,000 Ibfengine are presented. The maximum fuel
temperalure is3490 Kat .7 n_.front ehecore enlrance.
INSPI
Univr,sity of Florida
P&W XNR2000 Core Axial Flow Profile
Tc = 2750K Pc = 750psi F=250001bf
3,500
3,000
2.500
i
:_,0O0
1,500
E //""./. _.....::....I'....::....,.,..:.',..o..o.1.,
I..-
1,000
5O0
0
0 0.2 0.4 0.6 0.8 |
Normalized Length
Axial remperalure dislril,ulioel in XNR 2000core ispresenled. XNR 2000 fenlures i Iwo
path folded flow core fueled wilh CERMF.T. The maximum fuel temperature is3000 Kat
abou! 85% I'romthe enlrance Io the inner core region.
NIT': Systems Modeling (542 NP-TIM-92
INSPI-NTVR Core Axial Flow Profile
Tc = 2750K Pc = 750psi F=750001bf
3,000
2,500
_" 2,000
......... L....... _ ....... i.,I .... ,:,.,,su,.,.
to 1,500 ...... i', ........
E
Fe- 1,111111
i L , , , , I .... i , , , ,
0
0 0.2 0.4 0.6 0.8 1
Normalized Length
INSPI-NTVR Core Axial Flow Profile
Tc = 2750K Pc = 750psi F=750001bf
1.6
1.5
i 1.4
_ 1.1
1.3
1
0.9
0 0.2 0.4 0.6 0.8
Normalized Length
NP-TIM-92 (>43 NTP: SystemsModellng
INSPI-NTVR Core Axial Flow Profile
Tc = 2750K Pc = 750psi F=750001bf
0.22 iiiiiiiiiiiiiiiiiiiiiiii
0.2
0.18
iiiiiiiiiiiiiiiiiiiiiiiiiiiiiii_iil/i_i i iiii
._ 0.16
_ 0.14
Z
ti o.12
:E 0.1
0.08
0.06
0.04 .... ; .... i .... = .... i • . .
0 0.2 0.4 0.6 0.8
Normalized Length
INSPI-NTVR Core Axial Flow Profile
Tc = 2750K Pc = 750psi F=750001bf
7.6--:--_ .......... ........... i........... :...........
7 ___" .............
Q
5.5 ,
5 , , i . . , t .... i .... i ....
0 0.2 0.4 0.6 0.8
Normalized Length
NTP:System=Modeling 044 NP-'I'[M-92
Pump Pressure Rise vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
2,100
2,000
1,900
O
1,800
P
"! 1,700
v)
In
0) Chamber Temp.
?,- 1,600
¢).
E ....... j ........ _ 3000K
. _" --"-- 2750K
l_. 1,5OO
y • " 25I00K
1,41111 m • ...|I
1,300
6O0 700 800 900 1,000 1,100 1,200
Chamber Pressure (psi)
Specific Impulse vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
1,000
98O
Chamber Temp.
960
--,v--- 3000K
• "2750K
940 ................. "........................... --,F-- 2500K
o. _"-_'_v-_,_v.-_---,_v-,----,,,_,k._,,,. ___._.__ __
920 ....... ,........ _........ :......... ........ :........
000 ......................... :................... :........
+ : : :
880 ',":v-v ..... _;:v ..... v, v ; + v----
860 .... ; .... i .... ; .... J .... i ....
600 700 800 900 1,000 1,1O0 1,200
Chamber Pressure (psi)
NP-TIM-92 645 NTP: Systems Modeling
Core Exit Mach # vs Chamber Pressure
INPSI-NTVR @ 750001bf Thrust
0.28
0.26
0.24
'IV
0.22
:(E0
0.2
oO...l.O...l. ....
0.12 .... ' .... J .... _ .... ' .... i ....
600 700 800 900 1,000 1,100 1,200
Chamber Pressure (psi)
Turbine Pressure Ratio vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
1.26
1.18
1.16 ........ ----e--- XP00K
I- C--h_a--mber27T5e0m1(p.
1,14 ---v--- 25001(
1.12 .... ; .... i .... i .... i .... i .... I
600 700 800 900 1,000 1,100 1,200
Chamber Pressure (psi)
NTIP:SystemsModeling 646 NP-'rgq-92
Turbine Blade Speed vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
370
i -.......!......I.Y
360
35O
340
(/)
"O
330
Chamber Temp.
• 3000K
320
* " 275OK
!ii:iii '1
--v-- 2500K
310
t-
I--!- 300
.... i .... ; .... ; .... i .... ; ....
290
6OO 7oo eoo 9oo 1,000 1,100 1,200
Chamber Pressure (psi)
Turbine Blade Diameter vs Chamber Pressure
INSPI-NTVR @ 750001bf Thrust
0.235
o,,......i........i i..............,.y....
i 0.225 ................................
0.215
0.21 ........ i........ i ........ ' ........ !........ Chamber Temp.
0.205t......... :...... _-- ...... !......... 1--*-- 27soK
o.,! ::_ ..... il-'-_
i ', : 3000K
0.19
600 700 000 900 1,000 1,100 1,200
ChamberPressure(psi)
NP-TIM-92 647 NTP: SystemsModeling