重型燃气轮机高雷诺数CDA叶型转捩特性数值计算  

Numerical Calculation of Controlled Diffusion Airfoils of Transition Characteristics for Heavy-duty Gas Turbine at High Reynolds Number

作　　者：王润禾 童歆 羌晓青[2,3] 杜朝辉 欧阳华[1,3] WANG Run-he;TONG Xin;QIANG Xiao-qing;DU Zhao-hui;OUYANG Hua(School of Mechanical Engineering,Shanghai Jiao Tong University:Shanghai 200240,China;School of Aeronautics and Astronautics,Shanghai Jiao Tong University:Shanghai 200240,China;Engineering Research Center of Gas Turbine and Civil Aero Engine Ministry of Education,Shanghai 201306,China)

机构地区：[1]上海交通大学机械与动力工程学院,上海200240 [2]上海交通大学航空航天学院,上海200240 [3]燃气轮机与民用航空发动机教育部工程研究中心,上海201306

出　　处：《航空发动机》2023年第5期136-142,共7页Aeroengine

摘　　要：为研究重型燃气轮机的压气机叶片在高雷诺数工况下的气动性能,基于Gamma-Theta转捩模型的雷诺时均方程对某可控扩散叶型进行了数值计算。通过对比不控制马赫数与控制马赫数,分析高雷诺数对可控扩散叶型气动性能及转捩特性的影响。结果表明:在不控制马赫数条件下,在零攻角时,雷诺数从7×105增大为9×105,总压损失增加了约391.95%;在高雷诺数工况下随着雷诺数的增大,叶片流动损失不断增大,叶片可用攻角范围减小,同时在叶片吸力面出现激波,干扰转捩的产生。在控制马赫数条件下,当Ma=0.6时,在零攻角工况下,雷诺数从8.2×105增大为1×107,总压损失减小了约38.98%,吸力面转捩起始点从4.78%弦长处前移至1.11%弦长处;在高雷诺数工况下,叶片流动损失随着雷诺数的增大不断减小,吸力面转捩位置前移。In order to study the aerodynamic performance of compressor blades of heavy-duty gas turbines at high Reynolds number,numerical calculation of a controllable diffusion airfoil was conducted using the Reynolds time average equation based on the gamma-theta transition model.The effects of high Reynolds number on the aerodynamic performance and transition characteristics of controllable diffusion airfoils were analyzed by comparing the results of uncontrolled Mach number with that of controlled Mach number.The results show that without Mach number control,at zero angle of attack,the Reynolds number increases from 7×105 to 9×105,and the total pressure loss increases by approximately 391.95%.At high Reynolds number,with the increase of Reynolds number,the flow loss of the blade increases,and the range of available attack angle decreases.At the same time,shock waves appear on the suction surface of the blade,which interfere with the generation of transition.With Mach number control,when the Mach number is 0.6,at zero angle of attack,the Reynolds number increases from 8.2×105 to 1×107,the total pressure loss reduces by about 38.98%,the starting point of transition moves upstream from 4.78%to 1.11%chord length on the suction surface.At high Reynolds number,with the increase of Reynolds number,the flow loss of the blade decreases and the onset of the transition point moves upstream on the suction surface.

关 键 词：重型燃气轮机 高雷诺数 可控扩散叶型 马赫数控制 附面层转捩 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]