对转压气机动叶热态形变气动影响效应及冷热态叶型变换方法研究  

Effects of Blade Deformation on the Aerodynamic Performance and Hot-to-Cold Transformation Method of a Counter-Rotating Compressor

作　　者：王一勐 徐强仁 白素娟 赵巍[1,2,3] 赵庆军 徐建中[1,2,3] WANG Yimeng;XU Qiangren;BAI Sujuan;ZHAO Wei;ZHAO Qingjun;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 100049,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China;Beijing Key Laboratory of Distributed Combined Cooling Heating and Power System,Institute of Engineering Thermophysics,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,北京100049 [3]中国科学院轻型动力创新研究院,北京100190 [4]中国科学院工程热物理研究所分布式冷热电联供系统北京市重点实验室,北京100190

出　　处：《工程热物理学报》2024年第2期394-400,共7页Journal of Engineering Thermophysics

基　　金：国家科技重大专项(No.J2019-II-0016-0037);国家科技重大专项(No.J2019-II-0007-0027)。

摘　　要：为探究高负荷对转压气机动叶形变对气动性能的影响,采用热流固耦合计算方法分析了离心、气动及热载荷作用下的叶片形变规律,探索了形变下低压转子及对转压气机的气动性能变化机理,并进一步开展了冷热态叶型变换方法研究。结果表明:在总载荷作用下,低压转子和高压转子叶片前缘分别向吸力面和压力面方向形变,导致低压转子工作点向失速边界移动,对转压气机堵塞流量降低,峰值效率下降。通过采用基于虚功原理的逆向求解计算,可以在无需变形量反向插值和迭代修正下得到动叶的冷态叶型,进而实现设计的气动性能。To clarify the effect of blade deformation on the aerodynamic performance of a highly loaded counter-rotating compressor,a thermal-fluid-structure interaction method is used to analyze the character of the blade deformation and the variation mechanism of aerodynamic performance under centrifugal,aerodynamic,and thermal loads.Additionally,a method for hot-to-cold trans-formation is developed.The results show that the leading edges of the low-pressure rotor deform towards the suction sides,whereas the leading edges of the high-pressure rotor deform towards the pressure sides.This leads to the operating point of the low-pressure rotor moving to the stall bound-ary,and results in the reduction of choke mass flow and peak efficiency of the compressor.By using nonlinear static analysis with inverse solving,the cold blade profile can be generated to achieve the aerodynamic performance of the design point without the need for deformation reverse interpolation and iterative correction.

关 键 词：对转压气机 热流固耦合 叶片形变 冷热态变换 

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]