进口导叶角对叶根失稳压气机流动失稳的影响  

Influence of inlet guide vane angle on flow instability of hub instability compressor

作　　者：陈晓松 武文倩 潘天宇 李秋实[1,2,3] CHEN Xiaosong;WU Wenqian;PAN Tianyu;LI Qiushi(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Research Institute of Areo-Engine,Beihang University,Beijing 100191,China;Key Laboratory of Fluid and Power Machinery,Ministry of Education,Xihua University,Chengdu 610039,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学航空发动机研究院,北京100191 [3]西华大学流体及动力机械教育部重点实验室,成都610039

出　　处：《航空动力学报》2023年第1期215-222,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(51636001,51976005);国家科技重大专项(2017-Ⅱ-0005-0018)。

摘　　要：以一台航空高速压气机为研究对象,通过加装进口导叶调整压气机进气预旋角,采集失稳过程中的动态压力信号,观察不同导叶角度、流动失稳演化过程。结果表明:在负导叶角情况下,压气机由转子叶尖突尖波引起失稳;在零导叶角及较小的正导叶角情况下,由静子叶根区域的局部喘振诱发失稳;在较大的正导叶角情况下,静子叶根在节流过程中首先出现局部失稳,进一步节流导致叶尖旋转失速团出现,压气机完全失稳。分析认为,导叶角的增加通过降低反力度,调整了转静间的负荷分配,从而引起了失速初始扰动发生上述“转子突尖波-静子局部喘振-静子局部失稳”的转变。A high-speed aero-compressor with different instability precursors was taken as the research object. The inlet guide vane was installed to manipulate the compressor inlet pre-swirl angle.Several dynamic pressure transducers were arranged to measure the whole instability evolutions. The instability precursor and the evolutions were observed under different inlet guide vane angles. The results showed that at negative inlet guide vane angle, the compressor instability was caused by the spike in the rotor tip region. At zero inlet guide vane angle and small positive inlet guide vane angle, the instability was induced by the partial surge in the stator hub region. Under the condition of large positive inlet guide vane angle, local instability occurred at stator hub first in the process of throttling, and led to complete compressor instability with further throttling in form of rotating stall cells at the tip. The analysis showed that the increase of the inlet guide vane angle adjusted the load distribution between the rotor and the stator by reducing the degree of reaction, thus causing the instability precursors to change from “spike at rotorpartial surge at stator-local instability at stator” as described above.

关 键 词：航空压气机 流动稳定性 进气预旋角 失稳先兆 可调进口导叶 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]