Design Optimization of Non-Axisymmetric Vane for an Axial Compressor under Inlet Distortion  

作　　者：ZHANG Min DU Juan ZHAO Hongliang QIU Jiahui BA Dun CHEN Yang NIE Chaoqun 

机构地区：[1]Digital Twin Research Center,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing,100190,China [2]Key Laboratory of Advanced Energy and Power,Chinese Academy of Sciences,Beijing,100190,China [3]Innovation Academy for Light-Duty Gas Turbine,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》2023年第4期1321-1334,共14页热科学学报（英文版）

基　　金：The authors gratefully acknowledge the support of the National Science and Technology Major Project(J2019-II-0017-0038);the National Natural Science Foundation of China(NSFC 52206061);Science Center for Gas Turbine Project(P2022-A-II-002-001).

摘　　要：The flow field at the inlet of compressors is generally encountered combined total pressure and swirl distortion for either aircraft engine with S-duct or gas turbine with lateral air intake.This inevitably deteriorates compressor aerodynamic performance,including not only the efficiency or pressure ratio but also the operation stability.In order to conquer this issue,appropriate measures such as integrating flow control techniques and modifying inlet or compressor design are of benefits.Due to this motivation,this article develops a full-annular two-dimensional(2D)and a partial-annular three-dimension(3D)optimization strategy for non-axisymmetric vane design.Firstly,two numerical simulation methods for evaluating performance of full-annular 2D vane and compressor with partial-annular 3D vane are developed.The swirl patterns at the inlet of a 1.5-stage axial compressor are analyzed and parametrized,and the parameterization is transferred to characterize the circumferential distribution of geometrical parameters of the vane profile.These approaches dramatically reduce computational simulation costs without violating the non-axisymmetric flow distortion patterns.Then various full-annular 2D sections at different radial locations are constructed as design space.The designed vane is reconstructed and 3D numerical simulations are performed to examine performance of the non-axisymmetric vane and the compressor with it.Also,partial annular 3D optimization is conducted for balancing compressor efficiency and stall margin.Results indicate that the designed non-axisymmetric vane based on full-annular optimization approach can decrease the vane total pressure loss under the considered inlet flow distortion,while those using partial-annular optimization achieve positive effects on compressor stall margin.

关 键 词：combined total pressure and swirl distortion axial compressor non-axisymmetric vane OPTIMIZATION aerodynamic performance 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程] V232.4[航空宇航科学与技术—航空宇航推进理论与工程]