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Tapered inclined exhaust splitting seam structure for turbine blade trailing edge

A turbine blade and trailing edge technology, which is applied in the field of turbine blade trailing edge tapered exhaust slit structure, can solve the problems of large flow resistance, low cooling effect, and damage to the blade structure strength, so as to improve the flow rate, Effect of reducing flow resistance and loss and improving casting processability

Inactive Publication Date: 2020-03-27
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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  • Tapered inclined exhaust splitting seam structure for turbine blade trailing edge
  • Tapered inclined exhaust splitting seam structure for turbine blade trailing edge
  • Tapered inclined exhaust splitting seam structure for turbine blade trailing edge

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] Please refer to Figure 2. A turbine blade trailing edge tapering inclined exhaust splitting structure, comprising 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;

[0041] 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 air splitting channel 3, the exhaust splitting channel 3 at the trailing edge is a tapered structure, that is, a structure with a wide entrance and a narrow exit along the cold air flow direction, and the two boundaries of the exhaust splitting 3 at the trailing edge The angle formed by the line is the contraction angle ∠B of the exhaust splitting seam at the trailing edge; Line 5 is symmetrically distributed, and the typ...

Embodiment 2

[0043] A turbine blade trailing edge tapering inclined exhaust splitting structure, comprising 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;

[0044] The structural shape of the split rib 4 at the trailing edge is controlled by the centerline 5 of the rib, the width of the split rib 4 at the trailing edge is distributed symmetrically along the center line 5 of the rib, and the contraction angle ∠B of the vent channel at the trailing edge splits A typical value is 5°. The rib centerline 5 is an inclined (relative to the horizontal plane) straight line, and the width changes gradually from the cold air inlet end to the outlet end, so that the trailing edge exhaust slit 3 is a tapered channel with a certain contraction angle. The incident angle ∠A1 is the same as the exit angle ∠A2, which is an acute angle, with a typical value of 35°. At this time, the turning angle of the cold air ∠...

Embodiment 3

[0046] A turbine blade trailing edge tapering inclined exhaust splitting structure, comprising 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;

[0047] The structural shape of the split rib 4 at the trailing edge is controlled by the centerline 5 of the rib, the width of the split rib 4 at the trailing edge is distributed symmetrically along the center line 5 of the rib, and the contraction angle ∠B of the vent channel at the trailing edge splits A typical value is 20°. The rib centerline 5 is an inclined (relative to the horizontal plane) straight line, and the width changes gradually from the cold air inlet end to the outlet end, so that the trailing edge exhaust slit 3 is a tapered channel with a certain contraction angle. The incident angle ∠A1 is the same as the exit angle ∠A2, which is an acute angle, with a typical value of 25°. At this time, the turning angle of the cold air ...

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Abstract

The invention belongs to the technical field of aero-engine turbine cooling, and relates to a tapered inclined exhaust splitting seam structure for a turbine blade trailing edge. The inclined exhaustsplitting seam structure comprises a hollow turbine blade, an inner cavity cool air channel, a trailing edge exhaust splitting channel and trailing edge splitting seam partition ribs, wherein the inner cavity cool air channel is formed inside the hollow turbine blade, the trailing edge of the hollow turbine blade is provided with the trailing edge splitting seam partition ribs arranged side by side, and the trailing edge exhaust splitting seam channel is formed between the trailing edge splitting seam partition ribs arranged side by side for allowing cooling air to be discharged out of the blade and meanwhile carrying out air film coverage cooling on the blade trailing edge. According to tapered inclined exhaust splitting seam structure for the turbine blade trailing edge, the cool air canflow much smoothly, so that flow resistance and loss of the cool air in an cavity of the blade is reduced, and the flow resistance can be reduced by about 16%; and through designing an inclined exhaust trailing edge splitting seam into a tapered structure, the outflow speed of the cool air can be improved, internal convection heat exchange is strengthened, an air film coverage dead zone is reduced, in this way, comprehensive cooling effects of the blade trailing edge is further improved while blending loss is reduced, and heat exchange can be enhanced by about 8%.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine cooling, and relates to a turbine blade trailing edge tapered inclined exhaust slit structure. Background technique [0002] For aero-engines and gas turbines, increasing the gas temperature before the turbine can greatly improve the efficiency of the device, but because the ambient temperature of the gas is much higher than the current material's ability to withstand, it causes the cooling problem of the turbine blades. 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 ar...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/188
Inventor 吕东徐朋飞王晓放孔星傲王楠
Owner DALIAN UNIV OF TECH
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