高负荷跨声速涡轮激波损失机理及控制技术研究  

Research of Shock Loss Mechanism and Control Technology for Highly-loaded Transonic Turbine

作　　者：向欢[1] 陈云[2] 葛宁[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2014年第1期54-59,共6页Aeroengine

摘　　要：为了指导高性能、高负荷跨声速涡轮的设计,对其叶栅内的流场结构、尾缘波系结构、减小激波损失的机理及其控制技术进行了分析研究。结果表明:跨声速涡轮尾缘流场结构复杂,存在分离膨胀波、分离激波、基底区、再附激波、尾迹、吸力面反射波甚至激波边界层相互干扰等流动现象。通过采用收缩-扩张通道,喉道后采用直线型吸力面,减小吸力面尾缘弯折角、尾缘厚度和尾缘附近局部修型等措施,从而减弱激波强度,减小激波损失。In order to guide the design of high performance and loading for transonic turbine, the flow path in the transonic turbine cascade, the trailing edge shock structure, the mechanism and control technology of shock loss were studied. The results show that the trailing edge flow structure is complicated, existing the separating expansion wave, separating shock, base region, reattachment shock, wake, and shock boundary-layer interaction in the rear part of the transonic turbine. The strength and loss of the trailing edge shock decreased and reduced using the convergent-divergent throat passage, flat suction shape after the throat, reducing rear suction turning angle, thickness of trailing edge and local blade shape modification.

关 键 词：高负荷跨声速涡轮 尾缘激波 激波损失机理 损失控制技术 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]