轴流压气机插板式进气畸变数值仿真

张兴发; 李军; 宋国兴; 周游天; 谢豪

doi:10.13224/j.cnki.jasp.2019.05.022

轴流压气机插板式进气畸变数值仿真

doi: 10.13224/j.cnki.jasp.2019.05.022

空军工程大学航空工程学院等离子体动力学重点实验室,西安 710038

基金项目: 国家自然科学基金重点项目（51336011）

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出版历程
- 收稿日期: 2018-10-07
- 刊出日期: 2019-05-28

Numerical simulation on flat baffle inlet distortion of axial compressor

摘要

摘要: 以航空发动机稳定性评价体系中常用的插板实验为背景,分别进行低速、高亚声速、跨声速轴流压气机与插板畸变发生器的耦合数值仿真,研究插板畸变条件下压气机的流场特性以及不同类型压气机在插板畸变影响下的失速起始机制。研究发现：转子进口截面的周向流动是影响低速压气机稳定边界的主要因素；插板角涡对转子叶顶泄漏涡的扰动是影响高亚声速压气机稳定边界的重要原因；畸变气流影响下的叶片通道内激波强度和位置的变化是影响跨声速压气机稳定边界的关键因素。
- 轴流压气机 /
- 进气畸变 /
- 插板式畸变发生器 /
- 进气攻角 /
- 插板角涡
Abstract: The coupling numerical simulation of the low-speed, high-subsonic, transonic axial compressor with the flat-baffle-type distortion generator was carried out respectively. The flow field characteristics of compressor under the flat-baffle-type distortion condition and the stall boundary of the different types of compressors were analyzed. It was found that the circumferential flow in the inlet plane of the low-speed compressor, the influence of the flat baffle angular vortex on the high subsonic compressor tip leakage’s flow path, and the change of passage shock wave’s intensity and location in the transonic compressor rotor passage were important factors of distortion flow to the stability boundary of different types of compressor respectively.
- axial compressor /
- inlet distortion /
- flat-baffle-type distortion generator /
- inlet attack angular /
- flat baffle angular vortex

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参考文献(18)

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