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

ZHANG Bo; JI Hong-hu; ZHANG Zong-bin; LUO Ming-dong

doi:10.13224/j.cnki.jasp.2014.10.012

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

更新时间：2026-07-07

- Numerical investigation of effect of truncated cone with different cooling structures on infrared suppressing characteristics of nozzle cavities
- Issue 10, (2014)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.10.012
  CLC：
- Published：2014
- 稿件说明：
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张勃, 吉洪湖, 张宗斌, 罗明东. 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[J]. 航空动力学报, 2014, (10): 2362-2368. doi: 10.13224/j.cnki.jasp.2014.10.012

ZHANG Bo, JI Hong-hu, ZHANG Zong-bin, et al. Numerical investigation of effect of truncated cone with different cooling structures on infrared suppressing characteristics of nozzle cavities[J]. 2014, (10).
张勃, 吉洪湖, 张宗斌, 罗明东. 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[J]. 航空动力学报, 2014, (10): 2362-2368. doi: 10.13224/j.cnki.jasp.2014.10.012 DOI：

ZHANG Bo, JI Hong-hu, ZHANG Zong-bin, et al. Numerical investigation of effect of truncated cone with different cooling structures on infrared suppressing characteristics of nozzle cavities[J]. 2014, (10). DOI： 10.13224/j.cnki.jasp.2014.10.012.

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.

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.

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Related Author

ZHANG Bo

JI Hong-hu

ZHANG Zong-bin

LUO Ming-dong

LIN Lan-zhi

罗天培

刘瑞敏

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Related Institution

College of Power and Energy, Nanjing University of Aeronautics and Astronautics

System Engineering Department, Chengdu Institute of Aircraft Designing, Chengdou

中国航天科技集团有限公司航天推进技术研究院北京市航天动力试验技术与装备工程技术研究中心

中国航天科技集团有限公司航天推进技术研究院北京航天试验技术研究所

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