Air film cooling composite hole structure for turbine blade and turbine blade

Abstract

The invention belongs to the technical field of heat transfer and cooling of hot end components of gas turbines, and relates to an air film cooling composite hole structure for a turbine blade. The turbine blade comprises an air film hole plate and a thermal barrier coating arranged on the air film hole plate, a plurality of composite air film holes are formed in the air film hole plate, and a dumbbell-shaped groove is formed in the thermal barrier coating; and each composite air film hole comprises a spanwise expansion section and a straight hole section which communicate with each other, the straight hole sections communicate with an inner cooling channel of the turbine blade, and outlets of the spanwise expansion sections communicate with the dumbbell-shaped groove. The guiding effect of the dumbbell-shaped groove enables cooling air flow to be diffused in the groove in the transverse direction and the longitudinal direction, the jet flow momentum is weakened, and the spanwise covering capacity is greatly improved. In addition, the dumbbell-shaped groove changes the rotating direction of a kidney-shaped vortex pair, and the vortex pair develops towards the two sides of the groove under the compression action of main flow, so that the cold air jet flow is better attached to the wall surface; and the air film holes comprise the spanwise expansion sections at the outlets, so that the jet flow momentum can be further reduced, the diffusion of an air film in the groove is accelerated, and an excellent cooling effect is achieved.

Description

technical field [0001] The invention belongs to the technical field of heat transfer and cooling of gas turbine hot end components, and relates to a gas film cooling composite hole structure for a turbine blade and the turbine blade. Background technique [0002] With the rapid development of aero-engines, the temperature at the front inlet of the turbine continues to increase, and the temperature at the turbine inlet of advanced engines has reached about 2000K, which has far exceeded the temperature resistance limit of turbine blade materials. In order to ensure the safe operation of the turbine, various cooling technologies are used to cool the blades, mainly including internal cooling and external cooling. External cooling is also called film cooling, that is to extract part of the compressed air from the last stage of the compressor and bypass the combustion chamber directly into the turbine, so that the cooling air is sprayed from the inside of the blade to the side sur...

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the defects in the above-mentioned prior art, the object of the present invention is to provide a film cooling compound hole structure and a turbine blade for a turbine blade, which solves the problem that the spanwise diffusion ability of the film jet of the horizontal groove film hole is relatively large. low problem

Images