Air film cooling structure with surface recesses, turbine blade and turbine

Abstract

The invention provides an air film cooling structure with surface recesses. The cooling structure comprises a recess structure and an air film hole, and the air film hole is smoothly connected with the recess structure; airflow spreads to the recess structure through the air film hole to form an air film, and the air film spreads to the surface of a turbine blade; the recess structure comprises a first recess and a second recess, the second recess is arranged on the inner wall surface of the first recess, and the air film hole is formed in the inner wall of the second recess; an air film hole opening of the air film hole is provided with a rounding structure or a beveling structure; and / or the edge of the rear part of the first recess is provided with a rounding structure or a beveling structure. The invention further provides the turbine blade. Air film cooling structures arranged in an array manner are arranged on the wall face of the turbine blade. The recesses restrain reverse vortex pairs formed by air film flowing on the downstream wall surface; and the air film hole and the double-recess structure enable airflow flowing out of the air film hole to be tightly attached to the wall face. Compared with a conventional inclined hole, the air film cooling structure has the advantages that the air film cooling efficiency and the machining efficiency are higher, and the machining cost is lower.

Description

technical field [0001] The invention relates to the technical field of aeronautical generators and gas turbines, in particular to a film cooling structure with surface depressions, turbine blades and turbines. Background technique [0002] The gas temperature of aero-engines and gas turbines is as high as 1500-1900°C, far exceeding the allowable working temperature of metal materials. The high-temperature components of gas turbines, such as turbine blades, combustion chambers, etc., require internal convection cooling and external film cooling to maintain a suitable operating temperature for high-temperature components. In order to improve the thermal efficiency and working ability of aero-engines and gas turbines, the gas temperature of the engines is still increasing, and more efficient film cooling structures and film cooling technologies are urgently needed to maintain the wall temperature of the turbine blades within the allowable range, or Reduce cooling air usage. T...

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Problems solved by technology

[0008] Aiming at the defects in the prior art, the object of the present invention is to provide a film cooling structure, turbine blade and turbine with surface depressions, which solves the problem of film cooling in the prior art under the conditions of low blowing ratio and high blowing ratio Technical problems of low efficiency, high processing cost and difficult process

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