高压压气机叶栅的高速模型和低速模型的相似变换准则

本文以相似理论为基础 ,从线性小扰动方程、跨音小扰动方程和全扰动势方程出发 ,推导出一组在进口马赫数不同时 ,保持两组叶栅气动力相似的变换准则。变换涉及跨音与亚音 ,跨音和不可压 ,亚音与不可压及其全扰动的情形。应用二维和准三维无粘数值计算方法进行数值验证 ,证明了变换关系在无粘下的正确性。文中使用了局部线化概念和一些假设 ,其合理性一并由数值试验得到证实。本文在理论和数值试验上为压气机叶栅的高速模型和低速模型之间的相似变换提供了必要的基础。

SIMILARITY RULES FOR TRANSFORMATION BETWEEN HIGH-AND LOW-SPEED MODELS OF HIGH PRESSURE AXIAL COMPRESSOR BLADINGS

The similarty rules are based on general aerodynamic similarity theory and drived for the transformation between transonic and subsonic flows,transonic and incompressible flows,and subsonic and incompressible flows respectively,as well as in the cases of full disturbance,according to the linear small perturbation theory,the transonic small perturbation theory and the full potential equation.The validity of the similarity transformations under the inviscid assumption is verified by two dimensional and quasi three dimensional numerical simulations.The reasonableness of the basic concepts and assumptions used in the present work,such as local linearization concept,are testified by the numerical expeiments as well.This work provides an essential basis for the similarity transformation between the high and low spee models of high pressure axial compressors,and offers an approach to the profile design of a similarity low speed model and to applieation of experimental data of the similarity low speed model to the high speed high pressure axial compressor bladings.