摘要
根据风扇前缘曲线的相对前掠概念,将其应用于NASA67风扇叶片的改型,通过数值模拟研究了三种不同前缘曲线掠弯程度对叶片通道内气流流动的影响,计算结果表明。前掠叶片的等熵效率高于无掠叶片;前掠叶片的稳定工作裕度及流量范围比无掠叶片有很大提高,并随着前掠程度的增大而增大;前掠叶片的增压比低于无掠叶片,且增压比随前掠程度的增大而降低。
According to the conception of the forward sweep leading edge, this paper puts the design of forward sweep leading edge into the blade of NASA67 rotor. The Navier - Stokes equations, Baldwin - Lomax algebraic turbulence model, finite volume method and Runge - Kutta time stepping schemes are used in analyzing the effect on the performance of blade by the different forward degree of leading edge. The rather extensive computed results give three preliminary conclusions: (1 ) the efficiency of the forward sweep blade is higher than that of non-sweep blade; ( 2 ) the forward sweep blade can remarkably improve the stability and the scope of flux, and the influences are increasing with the increase of the forward sweep degree; ( 3 ) the pressure ration of the forward sweep blade is lower than that of the non-sweep blade, and the pressure ratio is decreased with the increase of the forward sweep degree.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2005年第1期11-13,共3页
Journal of Air Force Engineering University(Natural Science Edition)
关键词
前掠叶片
等熵效率
稳定性
增压比
forward sweep blade
isentropic efficiency
stability
pressure ratio
