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Inner cooling structure of bionic microchannel at front edge of turbine blade and forming method thereof

A technology of micro-channels and turbine blades, which is applied in the direction of blade support components, engine components, machines/engines, etc., can solve the problems of uneven cooling of steam cooling blades and insufficient cooling effect, so as to solve the problems of uneven cooling and cooling Insufficient efficiency, high cooling effect

Inactive Publication Date: 2015-11-04
XIAN UNIV OF TECH
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Problems solved by technology

[0004] The purpose of the present invention is to provide a bionic micro-channel internal cooling structure at the leading edge of the turbine blade to solve the problems of uneven cooling and insufficient cooling effect of the steam cooling blade in the high heat load area

Method used

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  • Inner cooling structure of bionic microchannel at front edge of turbine blade and forming method thereof
  • Inner cooling structure of bionic microchannel at front edge of turbine blade and forming method thereof
  • Inner cooling structure of bionic microchannel at front edge of turbine blade and forming method thereof

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Embodiment Construction

[0022] The present invention will be described in detail below in combination with specific embodiments.

[0023] The invention provides a bionic micro-channel internal cooling structure at the leading edge of a turbine blade, such as figure 1 As shown, including the blade 1, the outer layer of the blade 1 is the outer wall 2, the middle part of the blade 1 is provided with a blade central cavity 3, and the inner part of the outer wall 2 is provided with several groups of tree-like forked fine channels.

[0024] The tree-like bifurcated micro-channels are directly integrally formed by 3D printing.

[0025] Such as figure 2 As shown, each group of tree-like bifurcated micro-channels includes a micro-channel inlet 4 and several micro-channel outlets 5, and the micro-channel inlets 4 and micro-channel outlets 5 are respectively located on the upper and lower sides of the blade.

[0026] The air intake directions of the adjacent two groups of tree-like bifurcated micro-channels...

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Abstract

The invention discloses an inner cooling structure of a bionic microchannel at a front edge of a turbine blade. The inner cooling structure comprises a blade, wherein the outer layer of the blade is an outer wall; a blade center cavity is formed at the middle part of the blade; and multiple sets of tree branched microchannels are formed in the outer wall. The invention further discloses a forming method of the inner cooling structure. The inner cooling structure of the bionic microchannel at the front edge of the turbine blade adopts the tree branched microchannels designed by a bionics configuration theory, has the characteristics of high cooling efficiency, low flowing resistance and uniform temperature distribution, and can solve the problems of cooling nonuniformity and insufficient cooling efficiency of a steam cooling blade in a high-heat-load area.

Description

technical field [0001] The invention belongs to the technical field of steam cooling equipment for turbine blades, and in particular relates to a bionic micro-channel internal cooling structure at the leading edge of a turbine blade. The invention also relates to a forming method of the internal cooling structure. Background technique [0002] Heavy-duty gas turbines are the core equipment of advanced energy systems, and their cycle thermal efficiency and specific power increase with the increase of turbine rotor inlet temperature. At present, the initial temperature of advanced gas turbine turbines has far exceeded the temperature limit that blade materials can withstand. In order to prolong the safe service life of the gas turbine and ensure the normal operation of the turbine blades under high temperature conditions, the blades must be effectively cooled. Advanced blade cooling technology is a key measure to increase the initial temperature of gas turbine turbines. Its ...

Claims

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Application Information

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IPC IPC(8): F01D5/18B29C67/00B33Y10/00B33Y80/00
Inventor 税琳棋董坤坤高峰李艳
Owner XIAN UNIV OF TECH
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