|Table of Contents|

Design and numerical calculation of GH2/GO2 vortex-cooled combustion chamber(PDF)

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

Issue:
2010年05期
Page:
17-22
Research Field:
研究与设计
Publishing date:

Info

Title:
Design and numerical calculation of GH2/GO2 vortex-cooled combustion chamber
Author(s):
WU Dong-bo1;  LI Jia-wen1;  CHANG Ke-yu2
1 School of Astronautics，Beijing Univ. of Aeronautics and Astronautics，Beijing 100191，China
Keywords:
-
PACS:
V434
DOI:
-
Abstract:
Vortex cooling is a new type of thrust chamber cooling technology for the liquid rocket engine. This technology can simplify the thrust chamber structure, reduce cost and increase system reliability. In this paper, preliminary design of a vortex cooling based thrust chamber is performed. The numerical simulation of the designed thrust chamber is made by adopting PDF non-premixed combustion model and DO radiation model. The result shows that a bidirectional vortex is formed in the internal of thrust chamber and the wall temperature in the cylinder section of the thrust chamber is lower than 760 K. The average temperature of the cylinder wall is increased about 140 K but the maximum temperature is lower than 900 K while considering the radiation effect. Therefore, the technology of vortex cooling is feasible, but at the present the combustion efficiency is relatively low.

References:

[1]CHIAVERINI M J, MALECKI M J. Vortex combustion chamber development for future liquid rocket engine applications, AIAA 2002-4149[R]. USA: AIAA,2002. [2]FANG Dianqi, MAJDLANI Joseph. Hot flow model of the vortex-cooled wall liquid rocket, AIAA 2003-5055[R]. USA: AIAA, 2003. [3]MAJDLANI Joseph, FANG Dianqi. On the bidirectional vortex and other similarity solutions in spherical geometry,AIAA 2004-3675[R]. USA: AIAA, 2004. [4]唐飞, 李家文, 常克宇. 涡流冷却推力室中涡流结构的分析与优化[J]. 推进技术, 2010, 31(2): 165-169. [5]KARGAR Mahdi Msc, SAIDI Mohammad Hassan. Exper-imental investigation of heat transfer modes in vortex combustion engines, AIAA 2007-5586[R]. USA: AIAA, 2004. [6]MARTIN J. CHIAVERINIi, J. ARTHUR Sauer, et al. La-boratory characterization of vortex-cooled thrust chamber for methane/O2 and H2/O2, AIAA 2005-4131[R]. USA: AIAA, 2005. [7]周庭宇, 鲁雪生. 液氧过冷用热交换器的热力设计[J]. 低温工程, 2007 (3): 35-39. [8]栾叶君, 孙纪国, 田昌义, 等. 氢氧推力室再生冷却内壁故障分析[J]. 火箭推进, 2006, 32(5): 21-25. [9]滑利辉, 田维平, 甘晓松, 等. 喉栓式推力可调发动机喷管流场数值模拟[J]. 固体火箭技术, 2008, 31(4): 344-349. [10]陈建华, 杨宝庆, 周立新, 等. 人为粗糙度强化换热机理分析及效果评估[J]. 火箭推进, 2004, 30(4): 4-8.

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