截锥不同冷却结构对喷管腔体红外抑制特征影响的数值研究

张勃; 吉洪湖; 张宗斌; 罗明东

doi:10.13224/j.cnki.jasp.2014.10.012

截锥不同冷却结构对喷管腔体红外抑制特征影响的数值研究

doi: 10.13224/j.cnki.jasp.2014.10.012

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 成都飞机设计研究所总体设计部, 成都 610041

详细信息

作者简介:
张勃（1976- ），男，江苏南京人，副教授，博士，主要研究领域为强化传热、红外抑制.zhangbo_pe@nuaa.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2013-06-05
- 刊出日期: 2014-10-28

Numerical investigation of effect of truncated cone with different cooling structures on infrared suppressing characteristics of nozzle cavities

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Department of Conceptual Design, Chengdu Aircraft Design and Research Institute, Chengdu 610041, China

摘要

摘要: 对发动机喷管高温部件之一的截锥3~5μm波段上红外抑制特征进行了数值研究.在红外辐射信号较强的截锥前端布置气膜缝槽冷却结构和气膜孔冷却结构，将温度较低的外涵气流通过支板引入截锥，有效降低了截锥、支板的壁面温度和红外辐射强度.对两种冷却结构进行比较，结果表明，采用向下气膜缝槽冷却结构能够达到较好的红外抑制效果，但推力损失较大；采用气膜孔冷却结构，喷管红外抑制效果略有减弱，但推力损失较小.
- 红外抑制 /
- 喷管腔体 /
- 冷却 /
- 截锥 /
- 支板
Abstract: The characteristics of infrared suppressing on 3-5μm band of truncated cone, which was one of the high temperature components of engine nozzle were numerically investigated. Different arrangements of film cooling gap and film cooling hole structures were disposed on the truncated cone which showing strong infrared characteristics, and cold gas flowed into truncated cone through blades from by-pass channel, causing wall temperature drop of truncated cone and blades, furthermore, the infrared radiation intensity was depressed. By comparison of the two cooling structures, it is found that the method of film cooling gaps downwards can make wall temperature and infrared radiation intensity decrease more than that of film cooling holes, while lower thrust efficiency can be gotten.
- infrared suppressing /
- nozzle cavity /
- cooling /
- truncated cone /
- blade

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参考文献(18)

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