进气道-发动机匹配对压气机稳定性影响和扩稳方法研究

The main scope of this project is to carry on some relevant theoretical analysis and experimental investigation aiming at the match problem of inlet duct and aero-engine, which always cause diverse influences on the compressor performance. And another big concern of this project is to develop an effective stabilization method which can well extend the stable operating range but without side effects on the compressor performance under the circumstance of complex geometry inlet..Firstly, parameter research will be conducted based on the existing inlet duct patterns, through which the majority geometric parameters can be obtained. Experiments will be designed and performed with varying the geometry of the inlet duct on a low-speed fan rig and a transonic compressor rig. The effects of different inlet geometries on the compressor performance will be obtained via the steady measurements about the compression capability and efficiency and the unsteady measurements about the dynamic evolution of the inlet flow field and the stall process. This part of work is quite important for investigating the relationship between the inlet distortion at the inlet plane of compressor and geometry pattern of inlet duct, which is considered as the core for the intake-engine matching problem. .Then, a stabilization method based on the stall precursor-suppressed (SPS) casing treatment will be developed for the stability degradation caused by the complex geometry inlet ducts. Both model calculations and experimental tests will be contained in this project to search for the optimal structure parameters of the SPS casing treatment. Relevant research of this part can make a promising point for the stability control with the present of intake-engine matching problem..The purpose of this proposal is to further enrich people's understanding of the intake-engine matching problem, and to provide a reference for the aircraft engine integration design involved in the current model design and pre-research design of China.

进气道-发动机匹配问题是叶轮机气动热力学重要发展前沿，也是制约我国先进航空发动机自主研制的关键瓶颈问题，本项目拟针对由于进气道-发动机匹配问题引起的压气机气动性能衰退，尤其是稳定性大幅恶化开展理论分析和实验研究，并发展在复杂几何进气道环境下可以有效拓宽稳定裕度的扩稳手段。.针对典型的S形进气道引起的压气机进口旋流畸变和非均匀总压分布开展工作，提炼影响气动和稳定性的关键进气道几何参数，围绕进气道内畸变流场分布形式、动态演化特性等问题探究进气道形状对压气机气动性能和稳定性的影响规律。.基于自主发展的失速先兆抑制型（SPS）机匣处理开展进发匹配扩稳控制方法研究，发展不同进气道几何条件下SPS机匣处理理论设计方法，并在亚音/跨音压气机实验台上进行实验验证，探寻进气道-发动机匹配环境下兼具性能提升和高效扩稳的优化设计方法。

进气道-发动机匹配问题是叶轮机气动热力学重要发展前沿，也是制约我国先进航空发动机自主研制的关键瓶颈问题，本项目针对由于进气道-发动机匹配问题引起的压气机气动性能衰退，尤其是稳定性大幅恶化开展了理论分析和实验研究，并发展了在复杂几何进气道环境下可以有效拓宽稳定裕度的扩稳手段。.针对典型的S形进气道引起的压气机进口旋流畸变和非均匀总压分布开展了研究工作，提炼了影响气动和稳定性的关键进气道几何参数，围绕进气道内畸变流场分布形式、动态演化特性等问题探究了进气道形状对压气机气动性能和稳定性的影响规律。.基于自主发展的失速先兆抑制型（SPS）机匣处理开展了进发匹配扩稳控制方法研究，发展了不同进气道几何条件下SPS机匣处理理论设计方法，并在亚音/跨音压气机实验台上进行了实验验证，探寻了进气道-发动机匹配环境下兼具性能提升和高效扩稳的优化设计方法。