微型涡喷发动机蒸发管性能测燃烧室数值模拟

覃文隆; 樊未军; 张韬; 王伟俭; 张荣春

微型涡喷发动机蒸发管性能测燃烧室数值模拟

北京航空航天大学, 能源与动力工程学院, 航空发动机气动热力国家极重点实验室, 北京 100191

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出版历程
- 收稿日期: 2011-05-23
- 修回日期: 2011-09-16
- 刊出日期: 2012-04-28

Performance test of micro turbojet engine’s evaporator and numerical simulation of the combustor

National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 根据40daN级低成本弹用微型涡喷发动机燃烧室的性能要求,设计了一种蒸发管供油的环形燃烧室.文章先设计实验对蒸发管的雾化性能和蒸发率进行测试,再参照测试结果,运用计算流体动力学(CFD)方法对微型涡喷燃烧室进行数值模拟.计算结果表明,燃烧室设计合理,各项性能均达到了设计点要求.
- 微型涡喷发动机 /
- 蒸发管 /
- 性能测试 /
- 燃烧室 /
- 数值模拟
Abstract: An annular combustor supplied by evaporator for a micro turbojet engine which was used for 40daN level missile was designed.The evaporator’s atomization and evaporation rate data was obtaind by test and then used for the numerical simulation of the combustor.The CFD(computational fluid dynamics) simulation shows the structure of the combustor is reasonable and the performance meets the design point’s requirements.
- micro turbojet engine /
- evaporator /
- performance test /
- combustor /
- numerical simulation

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参考文献(12)

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