转静干涉对跨声速压气机叶片静气动弹性的影响  

Effects of Rotor-Stator Interaction on Static Aeroelasticity of a Transonic Compressor Blade

作　　者：汪松柏[1] 李绍斌[1,2] 宋西镇[1] WANG Song-bai LI Shao-bin SONG Xi-zhen(National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China)

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [2]先进航空发动机协同创新中心,北京100191

出　　处：《推进技术》2017年第2期341-347,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(51106003)

摘　　要：为了研究转静干涉对叶片静气动弹性的影响,采用时域双向流固耦合方法对1.5级跨声速压气机转子叶片在气动力和离心力共同作用下的变形过程进行了数值模拟,分析了设计工况下叶片的变形特征及其对气动性能的影响。结果表明:叶片变形明显改变通道激波位置和强度,最大绝热效率时均值较冷态叶型提高0.45%,堵塞流量增加了0.7%,气动特性线向流量增大方向偏移。气动力和离心力主要影响转子叶片轴向和周向的变形分量,转子叶片与导叶轴向间距缩短加剧了上下游叶片非定常气动干涉,转子前缘表面非定常压力波动幅值增加12.3%,周向变形使得转子前缘进口叶型角增大,上半叶高表面静压分布明显改变。高性能压气机工程设计中应该考虑叶片静气动弹性变形对气动性能的影响。In order to research the effects of rotor-stator interaction on static aeroelasticity of a compressor blade,a time domain two-way fluid-structure interaction numerical calculation method was applied to study the deformation process of a 1.5-stage transonic compressor rotor blade under aerodynamic and centrifugal forces,and the characteristic of deformation and its effects on the aerodynamic performance were analyzed in the design condition. The results show that the passage shockwave position and strength are altered due to the blade static deformation,the time-averaged peak efficiency increases by 0.45% compared with cold blade,and the choking flow rate increases by 0.7%,as a result,the aerodynamic characteristic map is shifted to a large mass flow direction. Aerodynamic and centrifugal forces have a major influence on the axial component and circumferential component,the axial spacing shortened between rotor and IGV blade rows can enlarge the unsteady effects,the pressure fluctuation amplitude increases by 12.3% on rotor blade leading edge,the circumferential deformation causes the inlet angle increasing,which changes the static pressure distribution on up half spanwise locations.The high-performance compressor design in industrial practice should consider the effects of blade static aeroelastic deformation on aerodynamic performance.

关 键 词：跨声速压气机 叶片变形 双向流固耦合 气动性能 非定常流动 

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]