A fold-line exhaust splitting structure for the trailing edge of a turbine blade

A turbine blade and trailing edge technology is applied in the field of the broken-line exhaust splitting structure of the trailing edge of the turbine blade, which can solve the problems of large flow resistance, damage to the blade structure, low cooling effect, etc., so as to improve the load resistance and improve the casting Craftsmanship, the effect of reducing cold air flow resistance and loss

Active Publication Date: 2021-11-05
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of trailing edge slit cooling structure has greater flow resistance and lower cooling effect, and also has a certain damage to the structural strength of the blade

Method used

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  • A fold-line exhaust splitting structure for the trailing edge of a turbine blade
  • A fold-line exhaust splitting structure for the trailing edge of a turbine blade
  • A fold-line exhaust splitting structure for the trailing edge of a turbine blade

Examples

Experimental program
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Effect test

Embodiment 1

[0036] Please refer to FIG. 2 , a turbine blade trailing edge broken-line exhaust splitting structure, including a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust splitting channel 3 and a trailing edge splitting rib 4;

[0037] The interior of the hollow turbine blade 1 is provided with an inner cavity cold air passage 2, and the trailing edge of the hollow turbine blade 1 is provided with side-by-side trailing edge split ribs 4, and the trailing edge split ribs 4 arranged side by side form a trailing edge row The gas splitting channel 3, the structure of the trailing edge splitting rib 4 forms a broken line shape, and its shape is controlled by the center line 5 of the rib, and the center line 5 of the rib is connected by at least two line segments with different angles, and wherein At least one section is inclined relative to the horizontal plane, and the width of the split rib 4 at the trailing edge is symmetrically distributed along the ...

Embodiment 2

[0039] Please refer to FIG. 2 , a turbine blade trailing edge broken-line exhaust splitting structure, including a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust splitting channel 3 and a trailing edge splitting rib 4;

[0040] The interior of the hollow turbine blade 1 is provided with an inner cavity cold air passage 2, and the trailing edge of the hollow turbine blade 1 is provided with side-by-side trailing edge split ribs 4, and the trailing edge split ribs 4 arranged side by side form a trailing edge row The gas splitting channel 3, the structure of the trailing edge splitting rib 4 forms a broken line shape, and its shape is controlled by the center line 5 of the rib, and the center line 5 of the rib is connected by at least two line segments with different angles, and wherein At least one section is inclined relative to the horizontal plane, and the width of the split rib 4 at the trailing edge is symmetrically distributed along the ...

Embodiment 3

[0042] Please refer to FIG. 2 , a turbine blade trailing edge broken-line exhaust splitting structure, including a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust splitting channel 3 and a trailing edge splitting rib 4;

[0043] The interior of the hollow turbine blade 1 is provided with an inner cavity cold air passage 2, and the trailing edge of the hollow turbine blade 1 is provided with side-by-side trailing edge split ribs 4, and the trailing edge split ribs 4 arranged side by side form a trailing edge row The gas splitting channel 3, the structure of the trailing edge splitting rib 4 forms a broken line shape, and its shape is controlled by the center line 5 of the rib, and the center line 5 of the rib is connected by at least two line segments with different angles, and wherein At least one section is inclined relative to the horizontal plane, and the width of the split rib 4 at the trailing edge is symmetrically distributed along the ...

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PUM

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Abstract

The invention belongs to the technical field of aero-engine turbine cooling, and relates to a broken-line exhaust slit structure at the trailing edge of a turbine blade. A turbine blade trailing edge broken-line exhaust splitting structure, comprising a hollow turbine blade, an inner cavity cold air channel, a trailing edge exhaust splitting channel and a trailing edge splitting rib; the hollow turbine blade is provided with an inner cavity cooling air Channels for low-temperature cooling gas to flow inside the blades to cool the blades. The trailing edge of the hollow turbine blade is provided with trailing edge split ribs arranged side by side, and the trailing edge split ribs arranged side by side form a trailing edge exhaust split channel. In the present invention, the exhaust splitting of the trailing edge is designed as an oblique folding line exhaust, which reduces the turning angle of the cooling air in the splitting slot, and the cooling air changes from one turning to two or more turnings, thereby reducing the inner cavity of the blade. The flow resistance and loss of cold air can reduce the flow resistance by about 19%.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine cooling, and relates to a broken-line exhaust slit structure at the trailing edge of a turbine blade. Background technique [0002] Increasing the gas temperature before the turbine can greatly improve the efficiency of aero-engines and gas turbines, but the current gas temperature before the turbine has far exceeded the limit of the materials used, so it is urgent to develop more effective turbine blade cooling technology. At present, the hollow design is generally adopted for the turbine blades, and the heat is taken away by the enhanced convection heat transfer of the cooling gas inside and the air film is formed to cover and isolate the gas heating when the blades are discharged. This is the main solution to the cooling problem of the turbine blades. Larger internal heat exchange area", "smaller cold air flow resistance", "higher heat exchange efficiency", "larger air film coverage...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/188
Inventor 吕东周亦胄王晓放孔星傲王楠
Owner DALIAN UNIV OF TECH
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