Investigation on the transpiration cooling of a liquid rocket nozzle

JIN Shao-shan; JIANG Pei-xue; SUN Ji-Guo

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Investigation on the transpiration cooling of a liquid rocket nozzle

更新时间：2026-07-07

- Investigation on the transpiration cooling of a liquid rocket nozzle
- Vol. 23, Issue 7, (2008)
- 作者机构：
  
  1. 清华大学热能工程系, 热科学与动力工程教育部重点实验室,北京,100084
  2. 北京航天动力研究所,北京,100076
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2008
- 稿件说明：
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JIN Shao-shan, JIANG Pei-xue, SUN Ji-Guo. Investigation on the transpiration cooling of a liquid rocket nozzle[J]. 2008, 23(7).
DOI：

JIN Shao-shan, JIANG Pei-xue, SUN Ji-Guo. Investigation on the transpiration cooling of a liquid rocket nozzle[J]. 2008, 23(7). DOI：

摘要

采用SSTk-ω湍流模型对液体火箭发动机喷管发汗冷却进行了全场耦合计算

考虑了不同孔隙率、变物性、可压缩性、多孔介质热弥散效应、微尺度流动以及传质等因素的影响

比对再生冷却分析了不同注入率对壁面温度、冷却效率以及边界层厚度的影响;结果表明平均注入率的增大使平均壁温以更大的比例降低

采用发汗冷却的喷管喉部不再是最高温的部位.将CFD计算结果分别与实验以及一维气动公式计算结果进行了比较

证实计算结果可靠.

Abstract

The SSTk-ω turbulence model was used to simulate the coupled whole field of the transpiration cooling of a Laval-nozzle of a liquid O2/H2 propellant rocket engine.The influences of porosity

variation property

compressibility

the thermal disperse effect of porous media

micro-scale flow and mass transfer were considered in the model.The influences of porosity on local blowing ratio

the wall temperature and the boundary layer thickness were analyzed and compared with the regenerative cooling.The results showed that the increase of average blowing ratio can decrease the average wall temperature with a larger proportion and for the transpiration cooling nozzle the throat is no longer the highest temperature point.The simulation results were compared with both the experimental results and the one dimension aerodynamics formula and approved to be accurate.

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Related Author

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Yufan XIE

Fei LONG

Qin LIU

Yidan CHEN

Hongyu CHEN

Yazhou LIU

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Related Institution

China Special Vehicle Research Institute，Aviation Industry Corporation of China，Limited

Airport Support Bureau，Air Force Logistics Department

Nanjing Puguo Technology Company，Limeted

National Key Laboratory of Science and Technology on Liquid Rocket Engines，Xi'an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation

Beijing Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation

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