跨声速压气机转子叶栅变静压比实验方法  

Experimental method of varying static pressure ratio for a transonic compressor rotor cascade

作　　者：魏巍 任思源 李学臣 时培杰 马护生 WEI Wei;REN Siyuan;LI Xuechen;SHI Peijie;MA Husheng(Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天技术研究所,四川绵阳621000

出　　处：《航空动力学报》2024年第11期160-169,共10页Journal of Aerospace Power

摘　　要：针对跨声速压气机平面叶栅变静压比实验问题,采用改变实验叶栅模型叶片数和调节背压的方式开展跨声速压气机转子叶栅实验方法研究,并基于计算流体力学(CFD)预测的叶片表面等熵马赫数分布发展了一种来流流场马赫数标定方法,并指导L030-4压气机转子叶栅近设计点的高静压比实验。研究结果表明减小叶片数和调节背压相结合的方法成功实现压气机叶栅变静压比的实验目的,模型7个叶片时可获得较好的实验效果;基于CFD的来流流场马赫数标定方法实现了L030-4压气机叶栅近设计点高静压比实验,获得的叶栅总压损失、静压比、出口气流角和轴向密流比参数同国外风洞实验数据相比,相对偏差均小于4%,验证了标定方法的合理性。The study focused on addressing the experimental challenge of increasing the static pressure ratio for transonic compressor rotor cascades.To this end,various experimental methods were investigated,including altering the blade numbers of the cascade model and adjusting the back pressure in a variable density plane cascade wind tunnel.A calibration method was developed to estimate the Mach number of the flow field,by utilizing the predicted isentropic Mach number distributions of blade surfaces obtained from computational fluid dynamics(CFD).This method effectively guided the high static pressure ratio experiments conducted near the design point of the rotor cascade of the L030-4 compressor.The results demonstrated the success of the combined approach,involving the reduction of blade numbers and adjustment of back pressure in achieving the desired high static pressure ratio conditions with seven blades.Furthermore,the Mach number calibration method based on CFD facilitated the realization of high static pressure ratio experiments near the design point of the L030-4 compressor cascade.The obtained parameters,including total pressure loss,static pressure ratio,exit flow angle,and axial density velocity ratio of the cascade,were compared with the experimental data from foreign wind tunnel experiments.The relative deviations were all below 4%,validating the rationality of the calibration method.

关 键 词：压气机 跨声速 超声速 转子叶栅 静压比 

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]