Gas film hole for gas turbine and blade for gas turbine

A gas turbine and air film hole technology, which is applied to machines/engines, blade support elements, mechanical equipment, etc., can solve the problems of poor air film coverage, reduced cooling performance and unit efficiency, and large amount of cooling air required.

Pending Publication Date: 2020-07-07
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the air film cooling method of the gas turbine blades in the prior art has the problems of poor air film coverage, low air film effectiveness, and a large amount of cooling air required, which reduces the cooling performance and unit efficiency

Method used

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  • Gas film hole for gas turbine and blade for gas turbine
  • Gas film hole for gas turbine and blade for gas turbine
  • Gas film hole for gas turbine and blade for gas turbine

Examples

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Embodiment Construction

[0032] Embodiments of the invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Back", "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inner", "Outer", "Clockwise", "Counterclockwise", "Axial", The orientation or positional relationship indicated by "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the referred device or element Must be in a particular orientati...

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PUM

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Abstract

The invention discloses a gas film hole for a gas turbine and a gas film hole for the gas turbine. The gas film hole comprises a gas inlet hole section and a gas outlet hole section, the first end ofthe gas outlet hole section communicates with the second end of the gas inlet hole section, the peripheral outline of the cross section of the air outlet hole section is roughly triangular and comprises a first arc section, a second arc section and a third arc section, the first arc section, the second arc section and the third arc section correspond to three corners of a triangle in a one-to-onemode, the second arc section and the third arc section are mutually symmetrical, every two adjacent arc sections of the first arc section, the second arc section and the third arc section are connected through a tangent line section, and the tangent line section connecting the second arc section and the third arc section is an arc section and is bent towards the first arc section. According to thegas film hole for the gas turbine, the required cold air amount can be reduced, then the cooling performance is improved, and therefore the unit efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to an air film hole for the gas turbine and a blade of the gas turbine with the air film hole. Background technique [0002] The gas turbine is the core equipment of natural gas, synthetic gas and other gas-fired power generation devices. The gas turbine mainly includes a compressor, a combustion chamber and a turbine. Among them, the turbine blades are the key components for converting the thermal energy of high-temperature gas into mechanical energy. According to the principle of Brayton cycle, the higher the temperature of the gas coming out of the combustion chamber, the higher the total thermal efficiency of the simple cycle of the gas turbine. However, when the high-temperature gas exceeds the turbine blade When the material is resistant to temperature, it seriously affects the life of the turbine blade. For this reason, in order to achieve high-efficiency power generati...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 殷宇阳刘润泽田一土陈强邓博周全凯翟芳芳
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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