一种设计亚音速叶型的解析方法

本文在近似于势、流函数的正交面上采用解析方法进行亚音速叶型设计。将改写后的无旋条件与连续方程联立求解,可在计算面上将叶型设计问题用标准拉普拉斯方程来表示。这一方法的优点是在流场计算中用解析解取代数值迭代计算过程,求解简便,节省计算机时,并为从理论上分析各种不同叶型的设计特性提供了便利条件。文中提供的算例表明,方法是有效和可行的。 

ANALYTICAL METHOD FOR SUBSONIC CASCADE PROFILE

A method of subsonic cascade design for axial flow compressor is provided as follows.The equations of continuity and quasi irrotationality are transformed into the potential stream function coordinates.Then a Laplace equation can be deduced for an aerodynamic parameter“Q”.The boundary conditions thereby are given as the distributions of velocity coefficients on the stagnation streamlines of both suction and pressure sides of a flow channal.The flow field is obtained from the analytical solution of the Laplace equation.Subsequently the field is turned back into the physical plane by diffierentiation and integration.Then the blade profile coordinates and the geometry of the cascade result from this analysis.The method has an advantage over other inverse methods in the fact that the flow field parameter“Q”can be easily obtained from the analytical solution of the Laplace equation instead of the numerical solution of a complex diffierential equation.So the method is easy to be programmed and to save computing time.To illustrate the validity of the design method,two compressor stator blade profile with subsonic inlet Mach number were designed and compared with the method presented in ref.3].The good agreement between the two methods show the applicability of this method.