摘要
提出了从叶片压力面到吸力面开孔射流延缓吸力面尾缘气流分离的思想,建立了考虑射流影响的叶片三维流场数值计算方法。以NASA67风扇叶片为原型进行开孔设计,通过数值模拟分析了开孔射流对该风扇叶片的流动特性、性能和稳定性的影响,初步研究表明经开孔射流处理能有效改善叶片吸力面尾缘的流动特性,从而提高压气机性能和稳定工作范围。
According to the idea which the jet flow from pressure surface to suction surface can lower and control separation of the boundary layer of the suction surface, this paper put the design of stiletto of the blade into NASA67 rotor. The Navier-Stokes equations, Baldwin-Lomax algebraic turbulence model, finite volume method and Runge-Kutta time stepping schemes are used for analyzing the effect to the performance of blade by the jet flow from pressure surface to suction surface. The rather extensive computed results give the preliminary conclusions： within a majority of the area of flux, jet flow can lower and control separation of the tail of suction surface, which can increase the efficiency and the stability of blade. The pressure ratio doesn＇t alter much.
出处
《空气动力学学报》
EI
CSCD
北大核心
2006年第2期152-156,共5页
Acta Aerodynamica Sinica
关键词
风扇
射流
附面层
性能
fan
jet flow
boundary layer
performance
