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Rotary cooling channel turbine blade adopting T-shaped partition wall

A technology for cooling channels and turbine blades, applied in the direction of blade support components, engine components, machines/engines, etc., can solve the problems of difficulty in further improving the cooling effect, insufficient contact between cold air and hot wall surfaces in the heat exchange area, and achieve favorable Cooling effect, long flow path, and improved cooling effect

Pending Publication Date: 2021-06-11
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when facing a new generation of aero-engines with higher gas temperature, this type of structure is limited by conditions such as limited heat exchange area and insufficient contact between cold air and hot wall surface, so it is difficult to further improve the cooling effect and cannot meet the demand, and further improvement is needed

Method used

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  • Rotary cooling channel turbine blade adopting T-shaped partition wall
  • Rotary cooling channel turbine blade adopting T-shaped partition wall
  • Rotary cooling channel turbine blade adopting T-shaped partition wall

Examples

Experimental program
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Effect test

Embodiment 1

[0024] The interior of the blade contains several cavities, and a rotary cooling channel with a T-shaped partition wall is used in the larger area in the middle of the blade. In the cavity of the rotary cooling channel with a T-shaped partition wall, there are chord partition walls and sub-channel partition walls, the thickness of the partition wall is δ=0.8mm; the distance between the sub-channel partition walls and the blade tip is d 1 = 4mm, the gap between the chord-wise partition wall and the blade root is d 2 = 4 mm. Chordal partitions and channel-dividing partitions divide the cooling channels into three chambers. The cavity close to the trailing edge of the blade surrounded by the back of the blade, the chord partition wall and the sub-channel partition wall is the dorsal rear cavity, with a height of l 1 ; The cavity close to the leading edge of the blade surrounded by the blade back, the chord partition wall and the sub-channel partition wall is the dorsal front ca...

Embodiment 2

[0026] Such as Figure 4 As shown, the interior of the blade contains several cavities, and a rotary cooling channel with a T-shaped partition wall is implemented in the larger area in the middle of the blade. Chordal partition walls and sub-channel partition walls are arranged in the cavity of the rotary cooling channel implementing T-shaped partition walls, and the thickness of the partition walls is δ=0.8mm. The gap between the partition wall of the sub-channel and the blade tip d 1 = 4mm, the gap d between the chordwise partition wall and the blade root 2 = 4 mm. The chord-wise partition walls and the channel-dividing partition walls divide the cooling channels into three chambers. The cavity close to the trailing edge of the blade surrounded by the back of the blade, the chord partition wall and the sub-channel partition wall is the dorsal rear cavity, with a height of l 1 ; The cavity close to the leading edge of the blade surrounded by the blade back, the chord part...

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Abstract

The invention belongs to the technical field of turbine blades, and relates to a rotary cooling channel turbine blade adopting a T-shaped partition wall. The interior of the blade structure is divided into four cooling channels in the direction from the leading air inlet edge to the trailing air outlet edge, and the rotary T-shaped partition walls are adopted in the second cooling channel and the third cooling channel; chordwise partition walls extending in the chordwise direction and sub-channel partition walls approximately perpendicular to the blade chordwise direction are arranged in the channels; and in the top view of the blade, the two partition walls are approximately vertically arranged and form a T-shaped partition wall, and each cooling channel is further divided into three cooling cavities by the T-shaped partition wall, namely a back side front cavity, a back side rear cavity and a basin side cavity. According to the rotary cooling channel turbine blade, the internal space of the blade is subdivided through the multiple partition walls, the cold air flowing distance can be prolonged, the rich inner cavity heat exchange area is formed on the side surfaces of the partition walls, and the heat exchange area is increased by about 30% compared with a conventional rotation structure.

Description

technical field [0001] The invention belongs to the technical field of turbine blades, and relates to a rotary cooling channel turbine blade using a T-shaped partition wall. Background technique [0002] Turbine blades, as the main parts of aero-engines, work in high-temperature, high-pressure, and high-velocity gas environments. The cooling problem is very prominent, which directly affects the efficiency and safety of the whole machine. In order to ensure the reliable operation of the turbine blades, the main solution is to adopt a hollow design, use cold air to enhance convection heat transfer inside the blades to remove heat, and form a covering gas film to isolate the heating of the gas when the blades are discharged. The focus and goal of blade cooling design are "larger internal heat transfer area", "smaller cold air flow resistance", "higher heat transfer efficiency", "larger air film coverage area", "impact on structural strength". Less damage", "lower processing an...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/188F01D5/186
Inventor 吕东姚玉海高凤树朱凯笛孔星傲孙一楠
Owner DALIAN UNIV OF TECH