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
引用本文: 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 W M, TIAN F C, YANG H C. Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off[J]. Acta Aerodynamica Sinica, 2022, 40(1): 92−100. doi: 10.7638/kqdlxxb-2021.0201
Citation: GAO W M, TIAN F C, YANG H C. Study on the matching between a two-dimensional supersonic inlet and an aero-engine during take-off[J]. Acta Aerodynamica Sinica, 2022, 40(1): 92−100. doi: 10.7638/kqdlxxb-2021.0201

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

  • 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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