高速风洞带动力模拟试验TPS短舱唇口设计

陶洋; 刘光远; 张兆; 郭旦平; 林俊; 熊能

高速风洞带动力模拟试验TPS短舱唇口设计

陶洋^1,2,
刘光远²,
张兆²,
郭旦平²,
林俊²,
熊能²

1.
中国空气动力研究与发展中心空气动力学国家重点实验室, 四川绵阳 621000
2.
中国空气动力研究与发展中心高速空气动力研究所, 四川绵阳 622700

基金项目: 国家自然科学基金(10972233)

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- 被引次数: 0
出版历程
- 收稿日期: 2012-05-28
- 刊出日期: 2013-05-28

Engine nacelle lip design for high speed TPS wind tunnel tests

1.
State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 622700, China

摘要

摘要: 利用计算流体动力学(CFD)技术分析了进气道质量流量差异对外表面压力系数分布的影响,并通过对发动机进气道唇口的反设计优化,使涡轮动力模拟器(TPS)试验时的外表面压力分布与真实质量流量下的压力分布基本一致.通过对发动机唇口修正,可提高2.4m跨声速风洞高速带动力模拟风洞试验的准度.
- 涡轮动力模拟器 /
- 短舱唇口设计 /
- 高速风洞试验 /
- 反设计优化 /
- 数值模拟 /
- 发动机进气道
Abstract: Computational fluid dynamics (CFD) was adopted to investigate the effects of mass flow rate difference on nacelle outer surface pressure coefficient distribution.Inverse design optimization technique was used in engine nacelle lip correction in order to adjust the turbofan propulsion simulators(TPS) outer surface pressure distribution to make it identical with that of the real engine.The engine nacelle lip inverse design method can be used in 2.4 m transonic wind tunnel to improve jet engine flow simulation test accuracy.
- turbofan propulsion simulators(TPS) /
- nacelle lip design /
- high speed wind tunnel test /
- inverse design optimization /
- numerical simulation /
- engine inlet

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参考文献(15)

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