涡流燃烧发动机燃烧室数值模拟

孙得川; 白荣博; 刘上

doi:10.15892/j.cnki.djzdxb.2011.02.030

弹箭与制导学报 >

2011 , Vol. 31 >Issue 2: 111 - 113,116

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.02.030

火箭技术

涡流燃烧发动机燃烧室数值模拟

孙得川 ,
白荣博 ,
刘上

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西北工业大学固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安 710072

孙得川(1973-),男,河北容城人,副教授,博士,研究方向:火箭发动机,计算流体力学。

收稿日期: 2010-09-25

网络出版日期: 2025-05-30

基金资助

国家863基金(2007AA0168);航天创新基金(CASC0309)资助

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Numerical Simulation of Vortex Cold-wall Rocket Combustor

SUN Dechuan ,
BAI Rongbo ,
LIU Shang

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National Key Laboratory of Combustion, Flow and Thermo-structure, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2010-09-25

Online published: 2025-05-30

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摘要

为研究涡流冷壁火箭发动机燃烧室内部的流动情况,分别采用RNGk-ε模型和雷诺应力模型对涡流冷壁发动机燃烧室流场进行数值模拟,确定采用雷诺应力模型能够较好的模拟冷态双旋涡流动。通过数值模拟得到了外层准自由涡,内层准强迫涡的Rankine组合涡结构。研究表明:数值模拟得到的流动结果比冷态模型更接近实际情况;三维效应在准自由涡区域比较明显,在强迫涡区域很小,总体上不影响燃烧室内的双旋涡流动结构。

关键词： 涡流冷壁推力室; 双旋涡结构; 数值模拟; RSM模型

本文引用格式

孙得川 , 白荣博 , 刘上 . 涡流燃烧发动机燃烧室数值模拟[J]. 弹箭与制导学报, 2011 , 31(2) : 111 -113,116 . DOI: 10.15892/j.cnki.djzdxb.2011.02.030

Abstract

In order to study the flow field of vortex cold-wall rocket combustor, two turbulent models were used and compared by using CFD software, RSM turbulent models can simulate the pressure distribution, swirl velocity and bidirectional vortex very well. The Rankine vortex structure was obtained through numerical simulation. The results show that the calculation results even more agree better real combustor than the theoretical model, and the 3-D effect is apparent in the free vortex but smaller in the forced vortex and will not influence the structure of bidirectional vortexes.

Key words： vortex cold-wall combustor; bidirectional vortexes; numerical simulation; RSM model

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参考文献

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