Rocket ignition demonstration tests using silane were performed at the Penn State Combustion Research Laboratory. A heat sink combustor with one injection element was used with gaseous propellants. Mixtures of silane and hydrogen were used as fuel, and oxygen was used as oxidizer. Reliable ignition was demonstrated using fuel lead and and a swirl injection element

Kincaid, Kevin

Pal, Sibtosh

Santoro, Robert

Watkins, William B.

English

NASA Technical Reports Server

Rocket Ignition Demonstrations Using Silane
Sibtosh Pal and Robert Santoro
Propulsion Engineering Research Center
Pennsylvania State University
State College, PA
and
William B. Watkins and Kevin Kincaid
Pratt and Whitney Liquid Rocket Engineering
West Palm Beach, FL
Abstract
Rocket ignition demonstration tests using sitane were performed at the Penn State
Combustion Research Laboratory. A heat sink combustor with one injection element was
used with gaseous propellants.
oxygen was used as oxidizer.
swirl injection element.
Mixtures of silane and hydrogen were used as fuel, and
Reliable ignition was demonstrated using fuel lead and a
Discussion
As part of the NASA/MSFC Advanced Reusable Transportation Technologies
Program, rocket ignition demonstration tests using silane were performed at Penn State's
Cryogenic Combustion Laboratory. A heat sink OFHC copper combustor with a uni-
element injector was used. The chamber cross-section was 0.875 x 0.875 in. square, and
the length from the injector face to the start of the nozzle converging section was 3.25 in.
Gaseous propellants were used for the tests. Oxygen was used as the oxidizer, and a fluid
supply system which enabled varying proportions of silane and hydrogen was used to
provide the gaseous ignition mixture. Nominal target ignition chamber pressure was
150 psia, however, this was varied as proportions of silane and hydrogen were changed.
Two types of injection elements were tested, a swirl element and a shear element. Both
silane/hydrogen lead and oxidizer lead timing sequences were tested.
Tests were performed by progranaming a candidate ignition sequence into the
laboratory control system and executing the programmed sequence. The time resolution
of the laboratory's control system is 0.l s. The combustor was monitored with video
cameras located in the cell, and video signals were recorded on video tape recorders.
Combustor pressure was measured with a pressure transducer connected to the
combustion chamber through a small connector tube. Propellant pressures and
temperatures were measured with pressure transducers and thermocouples close-coupled
to the propellant teed lines. Pressure and temperature data were recorded at 200 and
100 Hz, respectively, using the digital data acquisition system. Ignition was confirmed
by both visual observation of the combustion plume on video and increase in measured
. ,.2d
https://ntrs.nasa.gov/search.jsp?R=19990009078 2020-06-18T00:41:28+00:00Z
chamber pressure from non-conabusting to combusting conditions.
successful ignition test is shown in tigure 1.
A photo of a
Fioure 1. lo_niti0n with silane.
Oxidizer lead test results x_ith the s\_itl il\iector are sho\_ n in t]gcue " [-ests were
pertbrmed over the rat_._e of silane h._dro.gcn proportions 8()21) . silanet,,y dtogen mass
percentage < 100/0 t2c_ 80< silane hydrogen volume percentage < 100;0). FilLy-seven
tests were performed, x_ith ignition obser\ed for ten tests.
Results ot'silane hydrogen lead tests with the s_vhl h_.iector are sho_ n hi t_gure 3.
Tests were performed oxer the mnee 40 Orb.: silanehvdro,_,en pcrcenta,,e bx mass < 100'0
(4/96 < silane/tLvdroge_: percentage b\ xolume • 100(1). [hirt\-nine tests were
pertbrmed, with ienitieia obscrxcd iu thirt\ seven tests, lhc t\xe silanch?drogen lead
tests that did not ienite contained the Io\xcst proportion of silanc {4 '_) by volume!.
Ienition. tests xxith a coaxial iniech)r v_ere per*i,rmcd o_er the rmv,e=
60/40<silane'hxdro_e:: pcrcent:lgc b_ malss - I(){)¢)¢_)<)1 si[anchxdrogen volume
percent:_e < 1(_¢/,')1. I-:5 ,csul{s ,,f,,xidi,,cr and -diane hxdr,,_:'cn lead tests tbr tt_e shear
coat',:ial inicctor m'c sia,,,\_ in Fie< 4 ctnd <. tcspcclixcl\. ";c_c:: ,,: t_l_cc_, to-,t> shoxxed
lol11HOl'_
ii
O
Conclusions
Reliable, repeatable silane ignition was demonstrated over a wide range of
12 I
0/4 Ignition 1
10 "_k/
• 1
8
6 1012 IgniuOn ]
,v/
I
4
___lgnition]
2 ,=
I
0 _
80 82
Swirl Injector (Oxidizer Lead)
I011 Ignition[
\
4 |
84 86 88 90
012 Ignition [
6/16 Ignition I 12/3Ignition'
'\_i,
92 94 96 98 10
0/2 Ignition]
1113 Ignition
k'(O/F = 1.0)
!E,_/1 Ignition
O/F = 0.9
% Silane (mass)
Figure 2. Swirl injector oxidizer lead ignition results.
silane/hydrogen proportions using silane/hydrogen lead and a swirl injection element.
Oxidizer lead was not reliable with either injector. The shear coaxial element did not
e.'xhibit reliable ignition for either silane/hydrogen or oxidizer lead.
LL
0
0
9
8
7
6
5
4
3
2
1.1
0
Swirl Injector (Fuel Lead)
I2,2,_ition_4 [
• • t
' 313 Igmtlon I
II t2/2 Ignitionj
II
616 Ignition
/
616 Ignition (OF = 1.045) [-
4/4 Ignition (O/F = 1.0) /
I313 Ignition
II
I 2/2 Ignition I
X_, '_7/7Ignitioit
--I L212i_
30 40 50 60 70 80
% Silane (mass)
Figure 3. Swirl injector fuel lead ignition results.
90 100
4
65
4
14.
O3
0
Shear Coaxial Injector (Oxidizer Lead)
E
L
I
!
1-_2 Ignition I I
[-_ Ignition T
80 82 84
Figure 4.
86 88 90 92 94 96 98
% Silane (mass)
Shear coaxial injector oxidizer lead ignition results.
100
8
7
6
5
LI.
04
3
2
1
0
30 40
Shear Coaxial Injector (Fuel Lead)
Io,2 
I
2/3 Ignition
ii
3/5 Ignition 1
L1/1 Ignition
50 60 70 80 90
% Silane (mass)
FiCure 5. Shear coaxial injector fuel lead io.nition results.
100
5


Rocket Ignition Demonstrations Using Silane

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