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A New Type of Bifurcated Air Film Hole

A technology of air film holes and bifurcations, which is applied in the direction of machines/engines, blade support components, mechanical equipment, etc., can solve the problems of mainstream aerodynamic performance, lower engine efficiency, and difficult machining, etc., to increase air film coverage Smaller area, easier processing, and improved cooling efficiency

Active Publication Date: 2020-05-19
BEIHANG UNIV
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

However, these structures are relatively complex, which has a certain impact on mainstream aerodynamic performance, increases aerodynamic loss, and even reduces engine efficiency; and some special-shaped holes are difficult to machine and poor in realizability

Method used

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  • A New Type of Bifurcated Air Film Hole
  • A New Type of Bifurcated Air Film Hole
  • A New Type of Bifurcated Air Film Hole

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Embodiment Construction

[0029] Such as figure 1 As shown, the present invention is made up of a main air film hole 1 and two left air distribution film holes 2 and right air distribution film holes 3 distributed symmetrically with the main air film hole axis, the main air film hole 1 and the air distribution film hole The cross sections are all circular, and the diameter of the main air film hole is larger than that of the sub-air film hole. Among them, the left air distribution hole 2 and the right air distribution hole 3 are all connected with the main air film hole, and the left air distribution hole 2 and the right air distribution hole 3 are divided into two sections, and the front section and the main air film hole 1 have a development. To the included angle, the rear section is parallel to the main film hole 1. The structure of the left split air film hole 2 and the right split air film hole 3 is the main feature different from other air film holes, and it is also the reason why the new bifur...

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Abstract

The invention discloses a novel bifurcated air film hole. The novel bifurcated air film hole comprises a main air film hole body and branched air film hole bodies, the branched air film hole bodies comprise a left branched air film hole body and a right branched air film hole body which are symmetrically arranged on the two sides of the main air film hole body, the inlet end of the left branched air film hole body and the inlet end of the right branched air film hole body both communicate with the main air film hole body, an unfolding included angle is formed between the front section of the left branched air film hole body and the main air film hole body as well as between the front section of the right branched air film hole body and the main air film hole body, and the back section of the left branched air film hole body and the back section of the right branched air film hole body are both parallel to the main air film hole body. According to the novel bifurcated air film hole, compared with a traditional air film hole structure, the air film cooling performance can be significantly improved, and the cooling requirements of hot-end parts of an aero-engine are met.

Description

technical field [0001] The invention relates to the technical field of hot-end parts of aero-engines, in particular to a novel bifurcated gas film hole structure applied to hot-end parts of aero-engines. Background technique [0002] In order to improve the thrust-to-weight ratio and thermal efficiency of aero-engines, the temperature at the inlet of the turbine section is getting higher and higher, which has exceeded the temperature that metal materials can withstand. In order to reduce the thermal load of the hot-end components and ensure their normal operation, the cooling of the components becomes particularly important. At present, the common cooling methods for high-temperature components include film cooling, convective cooling, divergent cooling, and composite cooling. As one of the main cooling methods, film cooling technology plays an important role in effectively reducing the surface temperature and thermal stress of turbine blades. Continuous and in-depth resear...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D25/12F01D5/18
Inventor 罗翔曹楠李雪邬泽宇
Owner BEIHANG UNIV
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