سال انتشار: ۱۳۸۵

محل انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک

تعداد صفحات: ۸

نویسنده(ها):

Taghavi – Professor Assistance, Department of Mechanical Engineering, Iran University of Science and Technology
Shahryari – Master of Science, Department of Mechanical Engineering, Iran University of Science and Technology

چکیده:

A detailed numerical investigation is undertaken to understand and quantify the development of boundary layer on rotor baldes of a transonic axial compressor. The theory is based on solution of the full Navier-Stokes equations for a viscous, compressible and unsteady flow, together with Reynolds stress turbulence modeling. Interaction of shock wave with boundary layer and the subsequent flow separation are simulated. Analeses are performed for different values ofback pressures, incidences and freesteam turbulence intencities. Bounadry layer papremeters including displacement and momentumthicknesses, shape factor together with blockage and loss coefficients are calculated and discussed.