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Bead type turbine blade trailing edge slit cooling structure

A technology of turbine blades and cooling structures, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve the problems of reducing the temperature level of the trailing edge area of ​​the blade, and it is difficult to meet the cooling requirements of the trailing edge of the turbine blade. Cooling effect, increased convective heat transfer area, effect of increased convective heat transfer area

Active Publication Date: 2021-01-05
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As the temperature of the gas in front of the turbine continues to rise, the traditional split structure in the trailing edge is difficult to meet the cooling requirements of the trailing edge of the turbine blade. It is necessary to design a new and more effective cooling structure to reduce the temperature level in the trailing edge area of ​​the blade.

Method used

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  • Bead type turbine blade trailing edge slit cooling structure
  • Bead type turbine blade trailing edge slit cooling structure
  • Bead type turbine blade trailing edge slit cooling structure

Examples

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Effect test

Embodiment 1

[0031] Please refer to Figure 2, a rosary-style turbine blade trailing edge split cooling structure, including a hollow turbine blade 1, an inner cavity cold air passage 2 and a trailing edge exhaust split passage 3;

[0032] The interior of the hollow turbine blade 1 is provided with a cold air channel 2 in the inner cavity, and a plurality of discrete rosary-shaped trailing edge exhaust slit channels 3 are opened along the chord direction at the trailing edge, and its cross-sectional shape is circular or elliptical. The area changes continuously and alternately between the maximum value and the minimum value along the central line 4 of the slit channel, forming a rosary-like channel structure. Minor axis radius R of channel section x and major axis radius R y Controlled by the A-type wave curve 8 and the B-type wave curve 9 respectively. Typically, as shown in Figure 2(c), the centerline 4 of the split channel is a horizontal straight line in the front view of the blade, t...

Embodiment 2

[0034] Please refer to Figure 2, a rosary-style turbine blade trailing edge split cooling structure, including a hollow turbine blade 1, an inner cavity cold air passage 2 and a trailing edge exhaust split passage;

[0035] The interior of the hollow turbine blade 1 is provided with a cold air channel 2 in the inner cavity, and a plurality of discrete rosary-shaped trailing edge exhaust slit channels 3 are opened along the chord direction at the trailing edge, and its cross-sectional shape is circular or elliptical. The area changes continuously and alternately between the maximum value and the minimum value along the central line 4 of the slit channel, forming a rosary-like channel structure. Minor axis radius R of channel section x and major axis radius R y Controlled by the A-type wave curve 8 and the B-type wave curve 9 respectively. Typically, such as Figure 4 As shown, the center line 4 of the splitting channel is an inclined straight line in the front view of the bla...

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Abstract

The invention belongs to the technical field of aero-engine turbine cooling, and relates to a bead type turbine blade trailing edge slit cooling structure. The cooling structure comprises a hollow turbine blade, an inner cavity cool gas channel and trailing edge exhaust slit channels, the inner cavity cool gas channel is formed inside the hollow turbine blade and used for allowing low-temperaturecool gas to flow inside the blade to cool the blade; and the trailing edge of the hollow turbine blade is provided with the plurality of discrete bead type trailing edge exhaust slit channels in the chordwise direction so as to allow the cool gas to be exhausted out of the blade. The bead type trailing edge exhaust silt has a repeatedly contracted and expanded channel structure, the convective heat exchange area of the cool gas and a channel inside the trailing edge of the turbine blade is effectively increased, and compared with an existing trailing edge middle slit structure, the bead type trailing edge exhaust slit has the repeatedly contracted and expanded channel structure, and can blow off a boundary layer and inhibit the boundary layer from thickening, so that heat exchange is enhanced.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine cooling, and relates to a rosary-type turbine blade trailing edge slit cooling 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 commonly used for turbine blades, and the cooling gas is used to remove heat through the enhanced convection heat transfer inside the blades and form a gas film to cover and isolate the gas heating when exhausting the blades. This is the main solution to the cooling problem of turbine blades. [0003] The trailing edge area of ​​the turbine blade is heated by the gas on both sides of the blade basin and back side at the same time, and it is ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/187
Inventor 孔星傲吕东王楠刘英实康浩
Owner DALIAN UNIV OF TECH
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