Impact of circumferential inlet distortion on different types of stall inceptions in a transonic compressor  

作　　者：Tianyu PAN Jiandong YAN Hanan LU Qiushi LI 

机构地区：[1]Reserach Institute of Aero-Engine,Beihang University,Beijing 100191,China [2]School of Energy and Power Engineering,Beihang University,Beijing 100191,China [3]Key Laboratory of Fluid and Power Machinery,Ministry of Education,Xihua University,Chengdu 610039,China

出　　处：《Chinese Journal of Aeronautics》2024年第11期107-117,共11页中国航空学报（英文版）

基　　金：support of the National Natural Science Foundation of China(Nos.52322603,51976005,52006002,and 51906005);the Science Center for Gas Turbine Project,China(No.P2022-B-II-004-001);the Advanced Jet Propulsion Creativity Center,AEAC,China(No.HKCX2020-02-013);the National Science and Technology Major Project,China(No.2017-Ⅱ-0005-0018);the Fundamental Research Funds for the Central Universities,China(No.501XTCX2023146001);the Beijing Nova Program,China(No.20220484074);the Beijing Municipal Natural Science Foundation,China(No.3242016);the Collaborative Innovation Center for Advanced Aero-Engines,China。

摘　　要：The application of higher bypass ratios and lower pressure ratios significantly reduces specific fuel consumption with the development of turbofan engines.However,it also increases the risk of flow separation at the intake,leading to severe circumferential non-uniform inlet conditions.This study aimed to present an experimental investigation on instability evolutions of the compressor under circumferential non-uniform inlet conditions.Two stall inceptions regarding the different spatial scales and initial locations were selected to investigate this issue.The experiments were carried out on one tested rig,which the stall inceptions verified with the rotational speeds.At 65%design rotational speed(X),the stall inception was the spike,which was triggered by disturbances within serval pitches scale at the tip.Consequently,the spike-type stall inception was sensitive to circumferential distortion and led to a shrunk stall margin of the compressor.With the rotational speed increasing to 88%X,the stall inception switched to partial surge,which was induced by the flow blockage in the hub region around the full-annular.The results indicated that the partial surge was insusceptible to the circumferential distortion,which caused an extended stall margin with a lower stalled mass flow rate.In summary,the influence of distortion on the stability of the target compressor was found to be determined by the stall inception.

关 键 词：Partial surge Circumferential inlet distortion Transonic compressor Stall triggering event Loading distribution 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]