Combined cooling structure for turbine blade middle-part inclined impact aerating film

Abstract

The invention discloses an inclined impact and air film combination cooling structure used at the middle of the turbine blades of an aeroengine. The cooling structure is that: air film holes with the diameter of 1.0 mm-1.5 mm are arranged on the outer surface of the blade, the amount of the air film holes at each extension direction is 10-20, inclined impact holes are arranged inside the blades in the downstream area of the air film holes, the amount of the inclined impact holes equals to that of the air film holes, the angle of the impact holes is 30-45 degrees. The larger impact torque is generated through the inclined impact holes and a highly cooling area with the large area is formed inside the blades; at the same times, the air film holes outside the blades form an air film protection area to jointly realize the blade-cooling purpose. The results of the model test and the three-dimensional numerical simulation indicate that the cooling effect of the blades can reach 0.7 at least; at the same time, the pneumatic loss can be reduced distinctly and the flow resistance is distinctly lower than the ordinary turbine blades owing to the characteristic of cooling structure.

Description

technical field [0001] The invention relates to a combined cooling structure for obliquely impinging air-entrained film. The cooling structure is mainly used in the middle of the turbine blade of an aero-engine, and can produce a cooling effect of more than 0.7 to meet the cooling requirements of the aero-engine turbine blade. Background technique [0002] The most important performance index of an engine is the thrust-to-weight ratio. As people's performance requirements for the engine continue to increase, so do the requirements for the thrust-to-weight ratio. The most effective means to improve the thrust-to-weight ratio of the engine is to increase the gas temperature in front of the turbine. The pre-researched thrust-to-weight ratio 10 aero-engine before the turbine temperature is about 1850K ~ 1950K. However, the various materials currently used can only maintain their high strength indicators at about 1300 °C without cooling. Whether the turbine rotor can work safel...

AI Technical Summary

Problems solved by technology

Most of the conventional turbine blades currently designed are arranged with ribs of various shapes inside the blades to increase the internal disturbance and improve the heat transfer effect, and some air film holes with small diameters are often arranged on the outer surface of the blades. , forming full air film coverage, the cooling effect of turbine blades designed in this way is generally around 0.5, with the increase of gas temperature in front of the turbine, such cooling effect is obviously not enough for blade cooling, so efficient The invention of the turbine cooling structure is very important and urgent

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