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机译:
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beihang University;
Beihang University;
New Era Engineering Consulting Co., LtdShenyang Aeroengine Research Institute, Aero Engine Corporation of China;
Film cooling; Turbine blade; Suction surface; Compound angle; Hole arrangement; Blowing ratio;
机译:Study on the film cooling effectiveness of shaped holes in the suction surface gill region of the turbine blade
机译:Film cooling performance on pressure side of turbine blade with different number of hole rows under rotating state
机译:Film cooling of showerhead holes from the twisted leading edge of a gas turbine blade: Complex mainstream characteristics and reasonable angle arrangement