Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off

GAO Weimin; TIAN Fangchao; YANG Hanchao

doi:10.7638/kqdlxxb-2021.0201

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Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off

更新时间：2026-05-28

- Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off
- Vol. 40, Issue 1, Pages: 92-100(2022)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0201
  CLC： V235.1
- Published：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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Keywords

references

KOWALSKI E J. Computer code for estimating installed performance of aircraft gas turbine engines. Volume 1: Final report[R ] . NASA-CR-159691, 1979. https://ntrs.nasa.gov/api/citations/19800004788/downloads/19800004788.pdf

LIANG C Y, XIE Y P, LI Y F, et al. Application of integrated aircraft/engine technology in aeroengine designing[J]. Aeroengine, 2015, 41(3): 1-5. (in Chinese)

LIU Y Q, SHI L, LIANG C Y. Aerodynamic stability design method for certain aero-engine in whole engine's flight operating envelope[J]. Journal of Aerospace Power, 2012, 27(11): 2462-2467. (in Chinese)

COUSINS W T. History, philosophy, physics, and future directions of aircraft propulsion system/inlet integration[C]//Proceedings of ASME Turbo Expo 2004: Power for Land, Sea, and Air, Vienna, Austria, 2008: 305-320. doi: 10.1115/GT2004-54210

国防科学技术工业委员会. 航空涡轮喷气和涡轮风扇发动机进口总压畸变评定指, GJB/Z 64A-2004[S]. 北京: 中国标准出版社, 2004: 1-15.

国防科学技术工业委员会. 航空燃气涡轮发动机稳定性设计与评定指南, GJB/Z 224-2005[S]. 北京: 中国标准出版社, 2005: 1-36.

TIAN N, CHEN J G, ZHANG E H. Effect of distortion on aeroengine stability[J]. Aeroengine, 2002, 28(4): 25-28, 37. (in Chinese)

HAO B, ZHOU S T, ZHANG Z S, et al. Effect of total pressure distortion on aeroengine stability[J]. Aeroengine, 2012, 38(4): 34-37, 46. (in Chinese)

The Engineering Society for Advancing Mobility Land Sea Air and Space. Gas turbine engine inlet flow distortion guidelines, SAE ARP 1420B[S]. US: SAE Technical Standards Board, 2002.

The Engineering Society for Advancing Mobility Land Sea Air and Space. Inlet/Engine compatibility-from model to full scale development, SAE AIR 5687[S]. US: SAE Technical Standards Board, 2011: 1-94.

The Engineering Society for Advancing Mobility Land Sea Air and Space. Inlet total-pressure-distortion considerations for gas turbine engines, SAE AIR 1419A[S]. US: SAE Technical Standards Board, 2011: 10-279.

GAO W M, REN Z B, WANG Q, et al. Combination test and match characteristics research of an aircraft inlet/engine testbed[J]. Aeroengine, 2017, 43(4): 74-78. (in Chinese)

STEVENS C H, SPONG E D, HAMMOCK M S. F-15 inlet engine test techniques and distortion methodologies studies. Volume 1: Technical discussion[R ] . NASA-CR-144866, 1978. https://ntrs.nasa.gov/api/citations/19780022180/downloads/19780022180.pdf

BOWDITCH D, COLTRIN R. A survey of inlet/engine distortion compatibility[C]//19th Joint Propulsion Conference, Seattle, WA. Reston, Virginia: AIAA, 1983: 1166. AIAA-1983-1166. doi: 10.2514/6.1983-1166

YUHAS A J. , RAY R J, BURLEY R R, et al. Design and development of an F/A-18 inlet distortion rake: A cost and time saving solution[C ] //Biennial Flight Test Conference, Hilton Head, SC. Reston, Virginia: AIAA, 1994. AIAA 94-2132. NASA-TM-4722. https://ntrs.nasa.gov/api/citations/19960003993/downloads/19960003993.pdf doi: 10.2514/6.1994-2132

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