对转压气机内部流动机理及设计方法研究  

Counter-rotating compressor flow mechanism and aerodynamic design

作　　者：赵庆军[1,2] 周小勇 赵巍[1,2] 徐建中 ZHAO QingJun;ZHOU XiaoYong;ZHAO Wei;XU JianZhong(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学航空宇航学院,北京100190

出　　处：《中国科学：技术科学》2020年第10期1359-1375,共17页Scientia Sinica(Technologica)

基　　金：国家重点研发计划(编号:2016YFB0901402);国家自然科学基金(批准号:51790513)资助项目。

摘　　要：通过革新气动布局来提高压缩部件级压比是提高航空发动机推重比的重要途径.对转压气机在降低压气机轴向长度和重量,提高压气机级压比方面具有重要作用,正向着高负荷、高效率和宽稳定工作范围方向发展.本文开展了高负荷两级单转子压气机、1+1对转压气机、常规1/2+1对转压气机和激波增压对转压气机基元级分析,阐释了对转压气机的气动参数特点和实现级负荷提升的原理,指出高压转子采用进口反预旋和高圆周速度是实现加功量提升的有效手段.完成了具有相同进口轮毂比和流量的两级单转子压气机、1+1对转压气机、常规1/2+1对转压气机和激波增压对转压气机通流和三维气动设计,各压气机压比分别为3.0,3.0,3.0和5.0,平均级压比分别为1.73,1.73,1.73和2.24,高压转子进口相对马赫数分别达到1.18,1.02,1.40和1.88.对比分析了具有不同进口气流条件的压气机高压转子流场特征,重点分析了激波增压对转压气机高压转子的内部流动损失机理,结果表明激波诱导的边界层分离和叶顶泄漏流是高压转子的主要损失来源.针对高压转子的主要损失源,提出了叶片通道收缩比选取方法和反偏折叶型设计方法,抑制了结尾激波诱导的边界层分离;提出了叶型局部负曲率设计方法,抑制了前缘内伸激波诱导的边界层分离;建立了叶尖端弯设计方法,降低了叶顶泄漏流强度,有效提高了高压转子效率.针对激波增压对转压气机变工况气动性能衰减问题,建立了基于喉口面积调节和喉口附近机匣引气的高压转子起动方法,使高压转子能够在40%设计转速实现起动,改善了激波增压对转压气机在中、低转速下的工作特性.Improving the stage pressure ratio of compression components by reformatting the aerodynamic configuration is an important way to improve the thrust-weight ratio of aeroengines.Counter-rotating compressors improve the stage pressure ratio and reduce the axial length and weight of compressors.At present,counter-rotating compressors with high stage loading,high efficiency,and wide stable operating range are being developed.This paper presents an analysis on the elementary stage of a two-stage highly loaded single-rotor compressor,a 1+1 counter-rotating compressor,a conventional 1/2+1 counter-rotating compressor,and a counter-rotating ram compressor.The aerodynamic parameters and the mechanism of improving the stage loading of counter-rotating compressors are revealed.Adopting negative pre-swirl and high tip speed is an effective means to improve the power capability of the high-pressure rotor.The through flow and 3D aerodynamic design for the single-rotor compressor,the 1+1 counter-rotating compressor,the conventional 1/2+1 counter-rotating compressor,and the counter-rotating ram compressor with the same mass flow and inlet hub ratio are completed.For the above compressors,the pressure ratios are 3.0,3.0,3.0,and 5.0,respectively,and the average stage pressure ratios are 1.73,1.73,1.73,and 2.24 respectively.The inlet relative Mach numbers of the high-pressure rotor reach 1.18,1.02,1.40,and 1.88,respectively.The flow field characteristics of the high-pressure rotors of the above compressors with different inlet flow conditions are analyzed.The internal flow loss mechanisms of the high-pressure rotor of the counter-rotating ram compressor are analyzed.Results show that the main loss sources of the high-pressure rotor are the boundary layer separation caused by shock and the tip leakage flow.In consideration of the main loss sources of the high-pressure rotor,the design method of blade passage contraction ratio and reversely turning blade is proposed.This method suppresses the boundary layer separation caused by the te

关 键 词：对转压气机 激波 边界层分离 叶顶泄漏流 变工况特性优化 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]