Influence of Hub Contouring on the Performance of a Transonic Axial Compressor Stage with Low Hub-Tip Ratio  

作　　者：LI Xinlong LIU Shuaipeng GENG Shaojuan ZHANG Hongwu 

机构地区：[1]Advanced Gas Turbine Laboratory,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China [2]Innovation Academy for Light-Duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China [3]Key Laboratory of Advanced Energy and Power,Chinese Academy of Sciences,Beijing 100190,China [4]School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China

出　　处：《Journal of Thermal Science》2022年第1期179-188,共10页热科学学报（英文版）

基　　金：The authors gratefully acknowledge for the support of the National Science and Technology Major Project(2017-II-0006-0020,2017-II-0007-0021).

摘　　要：The rotor blade height with low hub-tip ratio is relatively longer,and the aerodynamic parameters change drastically from hub to tip.Especially the organization of flow field at hub becomes more difficult.This paper takes a transonic 1.5-stage axial compressor with low hub-tip ratio as the research object.The influence of four types of rotor hub contouring on the performance of transonic rotor and stage is explored through numerical simulation.The three-dimensional numerical simulation results show that different hub contourings have obvious influence on the flow field of transonic compressor rotor and stage,thus affecting the compressor performance.The detailed comparison is conducted at the rotor peak efficiency point for each hub contouring.Compared with the linear hub contouring,the concave hub contouring can improve the flow capacity,improve the rotor working capacity,and increase the flow rate.The flow field near blade root and efficiency of transonic rotor is improved.The convex hub contouring will reduce the mass flow rate,pressure ratio and efficiency of the transonic rotor.Full consideration should be given to the influence of stator flow field by hub contouring.

关 键 词：transonic compressor low hub-tip ratio hub contouring aerodynamics performance numerical simulation 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]