Heated wall surface cooling structure and gas turbine impeller vane with the same

Abstract

The invention relates to a cooling structure of the heated wall surface and a gas turbine blade of the cooling structure; wherein, the cooling structure comprises a compact wall surface layer, and a plurality of discrete through holes for the coolant to pass through are arranged on the compact wall surface layer; a porous coating is covered on the heated side of the compact wall surface layer to enable the porous coating and the compact wall surface layer with a plurality of discrete through holes to form a structure of double-layer superimposition, and the outlet of the discrete through hole is communicated with the porous coating. The porous coating can be continuously covered on the compact wall surface layer, and also can be covered on the local areas of the outlet of the discrete through holes. The invention has the advantages of synthesizing the characteristics of gas film cooling and transpiration cooling, fully combining the advantages of two cooling ways, effectively improving the cooling efficiency of the wall surface, reducing the geothermal gradient of the wall surface, and avoiding the continuous increase of the heat stress of materials. Simultaneously, the intensity of the cooling structure of the invention is enough to be used for common impeller machinery.

Description

technical field [0001] The invention relates to a cooling structure for a heated wall surface and a gas turbine blade using the cooling structure, belonging to the technical field of thermal engineering. Background technique [0002] Necessary cooling of mechanical structures in high-temperature environments to ensure safe operation of structures has always been a common problem in production and life. In applications involving heat engines, high-temperature surfaces that need to be cooled abound, such as cylinder walls of diesel and gasoline engines for vehicles, thrust chambers of rockets, blades of gas turbines, outer walls of ultra-high-speed aircraft, inner cylinders of super-combustion engines, etc. For gas turbines, increasing thermal efficiency and power means increasing turbine inlet temperature. The turbine inlet temperature, which has been increasing year by year, has exceeded 2000°C, while the maximum heat-resistant temperature of metal parts such as blades is g...

AI Technical Summary

Problems solved by technology

In short, the existing film cooling of gas turbines has the following deficiencies: limited cooling capacity; the use of discrete through holes leads to uneven cooling, correspondingly large thermal stress, and the material is prone to fatigue failure

Sweat cooling has the following disadvantages: the porous medium forming sweat cooling has poor strength; it is easy to cause overall failure due to local blockage

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