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Discrete air film cooling hole shape

A film cooling and hole pattern technology, which is applied to the support elements of blades, engine elements, machines/engines, etc., and can solve the problems of poor structural strength and difficult hole pattern processing.

Active Publication Date: 2013-08-14
中科合肥中型燃气轮机研究院有限公司
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AI Technical Summary

Problems solved by technology

However, most of the newly emerging pass types are not easy to process or have poor structural strength, so it is difficult to be practically applied on turbine blades

Method used

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Embodiment Construction

[0038] Figure 1a-1 , Figure 1a-2 It is the original ordinary cylindrical hole structure, and the length, diameter, and injection angle of the ordinary cylindrical hole are represented by L, D, and α, respectively. Coordinates X, Y, Z represent flow direction, transverse direction and radial direction respectively. Figure 1b-1 It is the basic form of a kind of discrete air film cooling hole type of the present invention, which is to Figure 1a-1 The subsidence and expansion treatment of the outlet of ordinary cylindrical holes, the subsidence depth, expansion length, and expansion width of the hole pattern are represented by H, B, and W respectively, and the angle of the gas outlet side of the subsidence structure is represented by β. Figure 1c-1 It is an evolution form of a discrete film cooling hole type of the present invention. On the basis of the basic form, an internal expansion boss structure is added between the downstream of the air outlet side of the cylindrical h...

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Abstract

The invention discloses a discrete air film cooling hole shape and relates to the technology of gas turbines. In the discrete air film cooling hole shape, a cylindrical hole outlet sinks for a depth from a cooled surface and is provided with an expanding structure starting at the center of the cylindrical hole outlet, the expanding structure is in bilateral symmetry with a cylindrical hole central line as the symmetrical axis, the sink depth H is 0.2-0.5 times of the diameter of a cylindrical hole, the expanding width W is 3-4 times of the diameter of the cylindrical hole, and the expanding length B is 1.0-2.0 times of the diameter of the cylindrical hole. The hole shape comprises: 1) a fundamental form; and 2) an expanded boss arranged in the space between the lower stream of an air outlet edge of the cylindrical hole and an air outlet edge of the expanding structure on the basis of the fundamental form. The discrete air film cooling hole shape has the advantages of being high in crosswise average air film cooling efficiency, good in cooling effect in high blowing ratio, less in pneumatic loss and easy to achieve. The discrete air film cooling hole shape is used in air film cooling of the gas turbines and is suitable for pressure surface, suction surface and end wall discrete hole air film cooling of turbine blades.

Description

technical field [0001] The invention relates to the technical field of gas turbines, and is a discrete film cooling hole type, which can improve the film cooling efficiency and film coverage of gas turbine blades, reduce the mixing loss of film cooling, and is suitable for film cooling with discrete holes s surface. Background technique [0002] Discrete hole film cooling is an efficient cooling technology widely used in gas turbine blades and endwall cooling. The basic principle is to introduce cooling air from the compressor to the turbine blades, and the cooling air flows out through the air film holes and covers the blade surface, so as to achieve the purpose of isolating the main flow of heat from the metal blade surface and reduce the blade surface temperature. The most basic hole type of discrete hole film cooling is cylindrical hole, which has the characteristics of simple processing and high structural strength, so it is most widely used in gas turbine blades. How...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
Inventor 安柏涛刘建军
Owner 中科合肥中型燃气轮机研究院有限公司
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