Off-Design Combustion in Liquid-Propellant Rocket Engine with High-Frequency Instability

Based on relative theories of gas dynamics and computational fluid dynamics, the flow field computation software ANSYS Fluent was used to simulate the steady flow field of the solid type ignition device of liquid-propellant rocket engine in two working conditions (condition I: without ignition channel, condition II: with ignition channel). On this basis, the influence of ignition channel on the working characteristics of the solid type ignition device of the liquid-propellant rocket engine was analyzed and experimentally tested. The results showed that when the pressure in the combustion chamber was atmospheric pressure, under condition II, the gas velocity at the throat of the ignition device did not reach the sonic velocity, and the position of sonic velocity moved to the downstream section of the ignition channel. Compared to condition I, the gas velocity and energy at the ignition outlet increased, which would be beneficial for initial ignition, and the gas pressure and temperature at the throat increased as well, indicating that the structural strength at the throat should be evaluated. The gas flow, gas pressure, and gas temperature at the ignition outlet decreased compared to working condition I, yet the changes were small and would have minimal effect on the ignition performance. During the pressure increase process in the combustion chamber, the gas pressure, velocity, temperature, flow, and energy at the ignition outlet experienced a steady stage in both working conditions before coming to an inflection point. The inflection point under condition II is smaller than that under condition I. To improve the ignition reliability, the working pressure of the ignition device should be further increased.

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Liquid-Propellant Rocket Engine Throttling: A Comprehensive Review

Journal of Propulsion and Power ◽

10.2514/1.49791 ◽

2010 ◽

Vol 26 (5) ◽

pp. 897-923 ◽

Cited By ~ 44

Author(s):

Matthew J. Casiano ◽

James R. Hulka ◽

Vigor Yang

Keyword(s):

Rocket Engine ◽

Liquid Propellant ◽

Comprehensive Review ◽

Liquid Propellant Rocket Engine ◽

Propellant Rocket

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Influence of Polyisobutylene Kerosene Additive on Combustion Efficiency in a Liquid Propellant Rocket Engine

Aerospace ◽

10.3390/aerospace6120129 ◽

2019 ◽

Vol 6 (12) ◽

pp. 129 ◽

Cited By ~ 1

Author(s):

Igor Borovik ◽

Evgeniy Strokach ◽

Alexander Kozlov ◽

Valeriy Gaponov ◽

Vladimir Chvanov ◽

...

Keyword(s):

Combustion Chamber ◽

Film Cooling ◽

Rocket Engine ◽

Combustion Efficiency ◽

Liquid Propellant ◽

Gaseous Oxygen ◽

Wall Film ◽

Measurement Results ◽

Liquid Propellant Rocket Engine ◽

Propellant Rocket

The combustion of kerosene with the polymer additive polyisobutylene (PIB) was experimentally investigated. The aim of the study was to measure the effect of PIB kerosene on the efficiency of combustion chamber cooling and the combustion efficiency of the liquid propellant for a rocket engine operating on kerosene and gaseous oxygen (GOX). The study was conducted on an experimental rocket engine using kerosene wall film cooling in the combustion chamber. Fire tests showed that the addition of polyisobutylene to kerosene had no significant effect on the combustion efficiency. However, analysis of the wall temperature measurement results showed that the use of PIB kerosene is more effective for film cooling than pure kerosene, which can increase the efficiency of combustion chamber cooling and subsequently increase its reliability and reusability. Thus, the findings of this study are expected to be of use in further investigations of wall film cooling efficiency.

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