SMALL-AMPLITUDE COMBUSTION PRESSURE OSCILLATIONS IN THE GAS ROCKET.

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Abstract:

The problem of small-amplitude, high-frequency, longitudinal combustion pressure oscillations in a rocket motor burning premixed gaseous propellants is the object of study of the analysis. Combustion zone chemical kinetics is found to be the driving mechanism of the phenomenon. A linearized, small-perturbation analysis is used to investigate the propagation of non-isentropic waves through the non-adiabatic flame zone. Effects of steady state chamber operating parameters on the amplification of oscillations are then presented with comparison to experimental trends. For example, in the equivalence ratio - chamber length stability plot a certain degree of correlation is noted. Author

Author(s):
Goede, P. J.
Author Organization(s):
JET PROPULSION CENTER PURDUE UNIV LAFAYETTE IND
Descriptive Note:
Technical memo.,
Pagination:
0074

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
TM-66-4, JPC-420
Contract/Grant Number(s):
AF-AFOSR-753-65, AF-AFOSR-753-66
Monitor Series:
66-0891
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means
Communities of Interest:
Weapons Technologies
Descriptor(s):
*ROCKET ENGINES, COMBUSTION, OSCILLATION, PRESSURE, GASES, REACTION KINETICS, PERTURBATION THEORY, PROPAGATION, FLAMES, NOZZLES, STABILITY
Field(s)/Group(s):
Combustion and Ignition, Rocket Engines, Rocket Propellants
Report Date:
1966 Jun 01