and internal nozzle. The assumptions that went into the combustion analysis .... pieces of the injection problem can be described analytically, the ensemble.
NASA-CR-192716
m
m
m
AN
EXTENDED
SUPERSONIC
DYNAMIC-ANALYSIS
COMBUSTION
OF
HYPERSONIC
MODEl,
VEHICLES
m
Interim
Task Renort
--
for NASA
Grant
On Research
NAG.I.]_41
Performed
for the
m
:
NASA
Langley
Research
Hampton,
Center
VA
,4" ,4" P,J I fe_ O_
O" O" C)
u_
U ,,,-4 C)
m
--
J.A.
Bo_ard, -Coi_e
f_
Principal
Dr. R.E. Aerospace
Investigators
Peck,
Research
of Engineering Arizona Tempe,
and
fe_
t.LJ :E I--
Dr. D.IL Schnrddt Center
and Applied
State University AZ 85287.8006
Sciences
oC O r3 t.t. t_ C3,,J ZW u_ O uJ_ o_' c'JL ,--4 o. oc )..
LU Z ZO k-
l-
Internal
Report
No.
March
1993
ARC93-2
_cQ
_J
4._ m
I CdZ I
_.,JuU C _--".,.tO I
M>I
jector
Isolator Duct
SupersonicCombuslor
Figure 2
Isolator Duct Geometry
FuelInjector
25 -30 %_increase
M>I
inarea
Fuel
.:::!:::::.:.:'
CyLinder
Figu_ 3 SupersonicCombustor Flame Holder
Cone (0.5- 1.5degreedivergence)
Diffuser
[_
Combustor
_1_
Intemal
Nozzle
_k
-I
-"'_-__\\\\\\\\\\\\\',_\\\\\_
_
A_ A_
_..=_° Isl
i
_
Fri_ion, Area Chm.ge, Mass Ai:ld.irion
Figure 4 _'amjet
Engine
A
3
Combustor
Mach
No. Distribution --o--Case
1 Case2
---c---Case 2.5
Z
---,---
Case4
2
1.5
1 0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
x/L Combustor Length Flgut¢5 Combustor
Mach Number Distribution
3
Combustor
Static
Temp.
DistribuUon
8OOO
7OOO
d.
---O---
Case !
---O--
Case 2
6OOO
50OO
4000
3OOO
20OO 0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
x/L Combustor
Figure 6 Combustor
Length
Static Tcmpemtur_
Distribution
1
Combustor 110000 IO0(XX) 9000O 80000
---O---
Case 1
+
Case 2
-----
Case3
--4---
Case4
Static Pressure
Distribution
70000 o
6(X)O0 50000 40000 !
3000O 2000O 0
0. I
0.2
03
0.4
0.5
0.6
0.7
0.8
x/L Combustor Length
Figure 7 Combustor Static Pressure Dislribution
0.9
l
Nozzle 470
'
I
Performance '
I
in a H2-O2
'
I
F-XtU_ ibfium i., -_en i ..'_/ 44O
.................... i:'........""......
J
tlf 410
. ...........................................
Rocket
'.._d____ ....
'.,
tal Res fits i
J
• .....................:......................4'.........._,'-" ""
i i
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,
•
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_o .......
ro.o,,°.o ..............
,o..ooo.o°.ooo°ooo..._..o...°,m,.o._
|
Frozen
J 380
=o.°..°.°
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,o.o°.o.°.,,.,o,,.oo,,_
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i !
.................
.,°.°
.........
°....................
o...........
_
_.o°_°._oo_
i
]
!
12
14
350 8
10
Hydrogen%,
16
18
20
by mass
Figure8 H2-O2 Rocket Performancemusummg Frozen and EquilibriumPerformanceLimitations
