二元外压式超声速进气道起飞过程的进发匹配特性

高为民; 田方超; 杨瀚超

doi:10.7638/kqdlxxb-2021.0201

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二元外压式超声速进气道起飞过程的进发匹配特性

专栏——内外流一体化技术 | 更新时间：2026-05-28

- 二元外压式超声速进气道起飞过程的进发匹配特性
- Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off
- 空气动力学学报 2022年40卷第1期页码：92-100
- 作者机构：
  
  中国航空发动机集团有限公司沈阳发动机研究所,沈阳,110015
- 作者简介：
  
  高为民（1964-），研究员，研究方向：飞机发动机一体化设计，进发匹配设计. E-mail：Gao_weimin@hotmail.com
  田方超*（1989-），工程师，研究方向：飞机发动机一体化设计，进发匹配设计. E-mail：603051443@qq.com
- 基金信息：
  
  航空动力基础研究项目
- DOI：10.7638/kqdlxxb-2021.0201
  中图分类号： V235.1
- 纸质出版：2022
- 稿件说明：
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高为民, 田方超, 杨瀚超. 二元外压式超声速进气道起飞过程的进发匹配特性[J]. 空气动力学学报, 2022, 40(1): 92−100.

GAO Weimin, TIAN Fangchao, YANG Hanchao. Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off[J]. 2022, 40(1): 92-100.
高为民, 田方超, 杨瀚超. 二元外压式超声速进气道起飞过程的进发匹配特性[J]. 空气动力学学报, 2022, 40(1): 92−100. DOI： 10.7638/kqdlxxb-2021.0201

GAO Weimin, TIAN Fangchao, YANG Hanchao. Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off[J]. 2022, 40(1): 92-100. DOI： 10.7638/kqdlxxb-2021.0201.

摘要

超声速进气道在起飞过程中存在一段特性较差的区域，表现为在零速度附近时进气道出口的总压恢复系数较低，总压畸变指数较高，对发动机高效、稳定工作带来不利影响，是进发匹配研究关注的重点问题之一。本文对一种带有辅助进气门的二元外压式超声速进气道开展进发联合试验和进气道CFD数值仿真，研究起飞过程中进气道流场结构、总压恢复系数、总压畸变指数随发动机转速的变化情况，通过流动机理分析提出了拆除防护网来改善进发匹配效果的技术措施，通过全尺寸进气道与发动机联合试验验证了改进措施的效果。同时，针对试验条件与真实飞行环境存在差别的问题，进行了地面效应影响的数值计算，给出了影响量值，为台架进发联合试验结果推广到飞行条件提供了依据。

Abstract

In the take-off stage

especially around the zero-velocity-state of aircrafts

supersonic inlets have a poor performance. Specifically

the total pressure recovery coefficient at the inlet exit is small and the total pressure distortion coefficient is large

which has a negative effect on the efficient and stable operation of aero-engines. Consequently

the inlet-engine matching during the take-off is one of the key problems that has received substantial attention. In this paper

experiments and numerical simulations by Computational Fluid Dynamics are used to study the matching between a two-dimensional supersonic inlet and an aero-engine. Flowfield structures in the inlet as well as the variation of total pressure recovery coefficient and total pressure distortion coefficient with the engine speed are analyzed. Results suggest that removing the protective net helps improve the performance of the inlet

which is further verified by an experiment of a full-size inlet and engine. Moreover

in view of the difference between the test conditions and real flight conditions

numerical analyses are performed to provide a basis for the extension of test results to flight conditions.

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references

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