The film cooling technologies can significantly improve the high temperature resistance of turbine blades. This paper focuses on film cooling technology

compares hole shapes at home and abroad

introduces the mechanism of the interaction between the main stream and the secondary flow

analyzes the influence of the cooling gas distribution on the film quality

and summarizes the effect of film cooling technology on aero-engine performance. A detailed discussion is carried out from the interactive flow field

hole shapes

hole accessory structure (tabs

slopes) and hole arrangements. There are four main routes for improving the cooling efficiency: (1) Reducing the strength of the kidney vortex; (2) Producing a pair of anti-kidney vortices; (3) Using groove structure; (4) Changing the outlet pressure distribution. Through the discussion and analysis of the hole shapes and accessory structures

it could provide guiding ideas for the optimal design of film cooling holes.