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Analysis on combustion stability of thrust chamber in high pressure hydrogen-oxygen rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2022年02期
Page:
66-75
Research Field:
目次
Publishing date:

Info

Title:
Analysis on combustion stability of thrust chamber in high pressure hydrogen-oxygen rocket engine
Author(s):
LIU Qian1; LI Jingxuan2; SUN Jiguo1; LIANG Xuanye2; XIANG Xiaolin2; PAN Liang1; ZHENG Mengwei1
(1.Beijing Aerospace Propulsion Institute, Beijing 100076, China 2.School of Astronautics, Beihang University, Beijing 100191, China)
Keywords:
high pressure hydrogen-oxygen rocket engine thrust chamber combustion stability numerical simulation flame transfer function
PACS:
V430
DOI:
-
Abstract:
Aiming at the structural scheme of the thrust chamber without baffle nozzle and acoustic cavity in high-pressure hydrogen-oxygen rocket engine, the combustion stability of the combustion chamber under different injection parameters and structural parameters was analyzed by using the method of decoupling of unsteady combustion and acoustic system.The unsteady Reynolds-averaged NS equation(URANS)was used to calculate the unsteady combustion process of the shear coaxial injector and obtain the flame transfer function, and the Soave Redlich Kwong(SRK)state equation was used to obtain density and so on. Considering that the flame length of the shear coaxial injector was equivalent to the magnitude of the sound wave, the distributed flame structure was used for modeling the flame transfer function.The combustion chamber acoustic modes loaded with the nozzle flame transfer function were calculated by COMSOL, and the combustion instability was predicted by combining the calculated mode frequencies and their growth rates.The results showed that the predicted combustion stability of the chamber was stable under different gas/oxygen injection velocity ratio, mixing ratio, relative nozzle pressure drop, retraction depth ratio and per-injection temperature under given operating conditions.In the thrust chamber design, it is beneficial to improve the combustion stability by increasing the gas/oxygen injection velocity ratio or reducing the mixing ratio in the combustion chamber.The work provides a reference for the design of injector in high-pressure hydrogen-oxygen rocket engine and the combustion stability evaluation.

References:

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