排气系统与尾机身一体化红外抑制器实验分析

唐正府; 张靖周; 王先炜; 刘强

排气系统与尾机身一体化红外抑制器实验分析

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国直升机设计研究所, 景德镇 333001

基金项目: 武器装备预研基金资助项目(编号:51410040304HK0201)

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- 被引次数: 0
出版历程
- 收稿日期: 2006-01-19
- 修回日期: 2006-07-03
- 刊出日期: 2007-02-28

Experimental research on infrared suppressor integrating the exhaust system with the tail part of a helicopter

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Helicopter Research and Development Institute, Jingdezhen 333001, China

摘要

摘要: 利用地面模拟实验件对排气系统与尾机身一体化红外抑制器模型进行了实验研究, 旨在分析引射混合与旋翼下洗对降低排气温度和目标的红外辐射特征的效果.结果表明, 通过波瓣喷管引射周围空气与主流燃气掺混冷却, 可以使高温燃气温度降低至少50%;利用旋翼下洗气流吹散热排气, 冷却尾机身模型壁面, 可以使模型壁面及尾焰在3-5μm和8-14μm的红外辐射强度分别降低39%和33%.另外, 简单的增大波瓣喷管的尺寸并不能够有效提高引射流量, 反而会使引射系数有所降低.
- 航空、航天推进系统 /
- 红外抑制器 /
- 波瓣喷管 /
- 旋翼下洗 /
- 引射系数
Abstract: Utilizing a ground test model,an experimental diagnostic study on the infrared suppressor integrating the exhaust system with the tail part of a helicopter has been performed to investigate the effects of ambient air pumping-mixing and rotor downwash on reducing the exhaust system temperature and diminishing the target infrared signature.The result shows that the gas temperature can be reduced by 50% at least by lobed nozzle which injects ambient air to mix with the hot gas;and rotor downwash flow that cools the tail part of the model will cause a decrease of total infrared radiation between 3-5 μm and 8-14 μm equivalent to about 39% and 33%.In addition,simply enlarging the lobed nozzle is not propitious to the enhancing of the entrained flux,while it will reduce the injection coefficient.
- aerospace propulsion system /
- infrared suppressor /
- lobed nozzle /
- rotor downwash /
- injection coefficient

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参考文献(8)

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