|Table of Contents|

Instability analysis on high-frequency injection-coupled combustion of shear coaxial injector(PDF)

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

Issue:
2014年03期
Page:
23-28
Research Field:
研究与设计
Publishing date:

Info

Title:
Instability analysis on high-frequency injection-coupled combustion of shear coaxial injector
Author(s):
TIAN Yuan;  LI Dan-lin;  SUN Ji-guo;  QIAO Gui-yu
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
shear coaxial injector;  combustion instability;  injection-coupling
PACS:
V434-34
DOI:
-
Abstract:
Shear coaxial injector is widely used in high thrust hydrogen/oxygen and LOX/LCH4 engines. According to investigation, the high-frequency injection-coupled combustion instability is easy to happen when the injection process of the central oxygen injector is coupled with acoustic oscillation in chamber. This instability can not be eliminated with baffle or acoustic cavity, but can be avoided by clever design of injector. Inherent acoustic frequency of oxygen injector was obtained by computing admittance of injector, and compared to the results of cold state acoustic experiment and subscale injector hot-fire test. Their consistency is quite good. The effects of oxygen injector length, oxygen injector orifice diameter, oxygen temperature, oxygen pressure on acoustic frequency of oxygen injector are investigated on this basis. The results indicate that the acoustic frequency of the oxygen injector can be improved if the oxygen injector orifice diameter is enlarged, the oxygen pressure is increased, the oxygen injector length is decreased or the oxygen temperature is lowered. Some suggestions on injector design are given.

References:

[1]杨 V, 安德松W E. 液体火箭发动机不稳定燃烧[M]. 张宝炯, 洪鑫, 陈杰, 译. 北京: 科学出版社, 2001.
[2]JENSEN R, DODSON H C, CLAFLIN S E. LOX/ hydrocarbon combustion instability investigation, NASA- CR-182249[R]. USA: NASA, 1989.
[3]KAWASHIMA H, KOBAYASHI K, TOMITA T, et al. A combustion instability phenomenon on a LOX/methane subscale combustor, AIAA 2010-7802[R]. USA: AIAA, 2010.
[4]NUNOME Y, ONODERA T. Combustion instability phenomena observed during cryogenic hydrogen injec- tion temperature ramping tests for single coaxial injector elements, AIAA 2011-6027[R]. USA: AIAA, 2011.
[5]BREISACHER K J, PRIEM R J. Analysis of 5 kHz combustion instabilities in 40 K methane/LOX combus- tion chambers, NASA Technical Memorandum 101368[R]. USA: NASA, 1988.
[6]BREISACHER K J. Axisymmetric single shear element combustion instability experiment, AIAA 93-1953[R]. USA: AIAA, 1993.
[7]AITHAL S M, LIU Z N, JENSEN R J, et al. Nonlinear injection transfer function simulations for liquid propellants, AIAA 2008-4742[R]. USA: AIAA, 2008.
[8]KAWASHIMA H, KUMAKAWA A, ONODERA T, et al. Combustion and regenerative cooling characteristics of LOX/methane engine, AIAA 2008-4837[R]. USA: AIAA, 2008.
[9]NUNOME Y, TAKAHASHI M, KUMAKAWA A, et al. High-frequency flame oscillation observed at a coaxial LOX/LH2 injector element, AIAA 2008-4848[R]. USA: AIAA, 2008.
[10]TSOHAS J, HEISTER S D. CFD simulations of liquid rocket coaxial injector hydrodynamics, AIAA 2009- 5387[R]. USA: AIAA, 2009.
[11]SWEENEY B A, LINEBERRY D M, FREDERICK R A, Jr. Scaling a single element atmospheric combustor. AIAA 2010-6893[R]. USA: AIAA, 2010.
[12]KOBAYASHI K, YU D, IIZUKA N, et al. Studies on combustion instability for liquid propellant rocket engines, AIAA 2011-6028[R]. USA: AIAA, 2011.

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