COOLING FLOW TECHNIQUE FOR DESIGNING AFTERBURNER HEAT SHIELDS

Lian Kangbao

Chinese

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COOLING FLOW TECHNIQUE FOR DESIGNING AFTERBURNER HEAT SHIELDS

更新时间：2026-07-07

- COOLING FLOW TECHNIQUE FOR DESIGNING AFTERBURNER HEAT SHIELDS
- Vol. 2, Issue 1, (1987)
- 作者机构：
  
  黎阳机械公司
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：1987
- 稿件说明：
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Lian Kangbao. COOLING FLOW TECHNIQUE FOR DESIGNING AFTERBURNER HEAT SHIELDS[J]. 1987, 2(1).
DOI：

Lian Kangbao. COOLING FLOW TECHNIQUE FOR DESIGNING AFTERBURNER HEAT SHIELDS[J]. 1987, 2(1). DOI：

摘要

用于某型歼击机上的发动机

设计要求其加力燃烧室内燃烧温度达1900K;长度约2.3m

外壁温度不超过1073K;一次工作寿命不小于150小时。根据国内实用机种状况

只有设计隔热屏才能满足壁温的要求。我们应用气膜冷却技术

半经验半理论的设计方法

很快地收到了予期的效果。本文仅扼要介绍设计思想及结果。

Abstract

By employing the air flow cooling technique

an afterburner heat shield was designed semi-empirically. It exhibited the desired advantages of long service life

low wall temperature and good performance. The cooling air flow accounted for 10% of the total airflow. The distribution of the cooling air was designed in referenceto successful designs. The practice of the aeroengine with the designed afterburner verifies that the presented technique is reliable.

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