Abstract: Film cooling is one of the most efficient cooling methods for turbine blades. A new type of slit cooling structure of turbine blades is proposed, numerical simulation is used to simulate the working process of turbine blades and the temperature and pressure parameters are obtained to analyze the effects of slit width, lip thickness and different machining positions on cooling efficiency and pneumatic loss. The results show that under the same incoming flow parameters, when the ratio of slit width to lip thickness is about 1.0, the new structure can achieve the best result; the top 60% of blade leading edge is the best machining position.

Key words: turbine blade, film cooling, slit type cooling, cooling efficiency