Boundary layer characteristics on rotor blades of transonic axial compressors
عنوان مقاله: Boundary layer characteristics on rotor blades of transonic axial compressors
شناسه ملی مقاله: ISME14_557
منتشر شده در چهاردهمین کنفرانس سالانه مهندسی مکانیک در سال 1385
شناسه ملی مقاله: ISME14_557
منتشر شده در چهاردهمین کنفرانس سالانه مهندسی مکانیک در سال 1385
مشخصات نویسندگان مقاله:
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
خلاصه مقاله:
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
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 of back pressures, incidences and freesteam turbulence intencities. Bounadry layer papremeters including displacement and momentum thicknesses, shape factor together with blockage and loss coefficients are calculated and discussed.
کلمات کلیدی: Axial Compressor – Cascade - Boundary Layer - Shock Wave - Blockage
صفحه اختصاصی مقاله و دریافت فایل کامل: https://civilica.com/doc/27989/