Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled

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

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Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled

更新时间：2026-07-07

- Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled
- Vol. 27, Issue 3, (2012)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,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：
  CLC：
- Published：2012
- 稿件说明：
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ZHANG Bo, JI Hong-hu, ZHANG Zong-bin, et al. Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled[J]. 2012, 27(3).
DOI：

ZHANG Bo, JI Hong-hu, ZHANG Zong-bin, et al. Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled[J]. 2012, 27(3). DOI：

摘要

航空发动机高温部件是发动机3~5μm上的重要红外辐射之一

对高温部件之一的中心锥的红外抑制技术进行了数值研究.在中心锥前端布置气膜缝槽

缝槽几何参数经过优化设计

将部分外涵低温气流经过支板引入中心锥

对支板和锥体壁面形成冲击冷却

在锥体前端形成气膜覆盖

使得支板与中心锥壁面得到了有效冷却

两者平均温度分别降低21.1%和46.2%

冷却气量约为外涵流量的1.6%.喷管腔体3~5μm波段上红外辐射得到有效抑制

喷管正后方红外辐射相比原型喷管降低30%

0°~45°范围内红外辐射则明显降低.

Abstract

Numerical investigation was performed on the infrared suppress characteristics of the nozzles with and without cone cooled.In the former

cone and blade were cooled by secondary channel gas

and the temperatures of blade and cone walls were effectively decreased by 21.1% and 46.2% respectively

using only 1.6% of the secondary gas.The radiation of nozzle cavity in 3~5μm was suppressed effectively

the radiation in the small view angle range from behind the nozzle decreased obviously

and the radiation decreased by 30% from straight behind the nozzle compared to the nozzle without cone cooling.

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Related Author

ZHANG Bo

JI Hong-hu

ZHANG Zong-bin

LUO Ming-dong

WANG Mei-juan

SONG Shuang-wen

HU Hao-sheng

PENG Jian-yong

Related Institution

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

Department of Conceptual Design, Chengdu Aircraft Design and Research Institute

China Aviation Powerplant Research Institute, Aviation Industry Corporation of China

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

China Aviatio n Powerplant Research Instit ute, Zhuzho u

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