Through seam type half-split seam trailing edge cooling structure and turbine blade

Abstract

The invention provides a through seam type half-split seam trailing edge cooling structure, which is arranged in a turbine blade trailing edge area and is formed by cutting off part of the wall surface of a turbine blade trailing edge pressure surface, only reserving the wall surface on one side of a suction surface and arranging a plurality of separation ribs. Through seams in the flowing direction of cooling airflow are formed in the separating ribs; and the center line of the through seams is parallel to the center line of a trailing edge cold air inlet cavity. According to the cooling requirements on the separation ribs, the rectangular cooling holes are formed in the separation ribs, the cooling airflow is divided into two parts at the outlet of the trailing edge cold air cavity, the main part cools the surface of a crack through the outflow seams, and the remaining part cools the separation ribs through the rectangular cooling holes, the cooling airflow and convection heat exchange in the separation ribs to separate the separation ribs; meanwhile, internal heat exchange with the inner wall surface of the trailing edge suction surface is enhanced, the heat exchange strength between the separation ribs and the suction surface side is enhanced, and the overall comprehensive cooling effect of the trailing edge is improved. Meanwhile, the adopted separation rib cooling holes are simple in structure and convenient to machine, and have good implementability.

Description

technical field [0001] The invention belongs to the technical field of gas turbine blade cooling, and in particular relates to a through-slit half-slit trailing edge cooling structure. Background technique [0002] Supersonic cruise without afterburner is one of the most important technical features of the fourth-generation fighter. To realize this technology, the temperature in front of the turbine needs to be further increased. Compared with the previous generation fighter jets, the heat load of the fourth generation fighter jets will increase significantly, so more and more attention is paid to efficient cooling system design. As a typical slit cooling area, the trailing edge of the turbine blade is the most challenging to carry out cooling design here, because the trailing edge area is relatively small and thin, and the heat load on both the pressure surface and the suction surface is large. Therefore, as the gas temperature increases significantly, seeking a cooling st...

AI Technical Summary

Problems solved by technology

[0006] Aiming at the problem that the cooling of the surface of the partition rib is neglected in the design stage of the trailing edge cooling structure in the prior art, and the cooling of the side near the suction surface of the trailing edge is not perfect, resulting in low cooling efficiency of the surface of the partition rib, the present invention proposes a through-slit Half-split trailing edge cooling structure

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