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Turbine blade trailing edge slit cooling structure adopting wavy partition ribs

A technology for 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, and enhanced heat transfer capacity

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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  • Turbine blade trailing edge slit cooling structure adopting wavy partition ribs
  • Turbine blade trailing edge slit cooling structure adopting wavy partition ribs
  • Turbine blade trailing edge slit cooling structure adopting wavy partition ribs

Examples

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Effect test

Embodiment 1

[0035] Please refer to Figure 2. A turbine blade trailing edge slit structure adopting wave-type ribs, comprising a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust slit channel 3 and a trailing edge slit rib 4;

[0036] The hollow turbine blade 1 is provided with a cold air channel 2 in the inner cavity, and a wave-shaped trailing edge exhaust slot 5 is opened along the chord direction at the trailing edge, and a plurality of wave-shaped trailing edge slots are evenly arranged inside it. The partition ribs 4 are arranged side by side to form discrete trailing edge exhaust slit channels 3 . Along the chord direction, the channel is in the shape of a wave with gradually attenuating amplitude and width, and its shape can be controlled by the central line 6 viewed from the slit. Typically, the centerline is designed with two peaks and troughs in the top view dimension, and its amplitude A x 0.3 times the thickness of the local leaf shape, ampl...

Embodiment 2

[0038] Please refer to Figure 2. A turbine blade trailing edge slit structure adopting wave-type ribs, comprising a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust slit channel 3 and a trailing edge slit rib 4;

[0039] The hollow turbine blade 1 is provided with a cold air channel 2 in the inner cavity, and a wave-shaped trailing edge exhaust slot 5 is opened along the chord direction at the trailing edge, and a plurality of wave-shaped trailing edge slots are evenly arranged inside it. The partition ribs 4 are arranged side by side to form discrete trailing edge exhaust slit channels 3 . Along the chord direction, the channel is in the shape of a wave with gradually attenuating amplitude and width, and its shape can be controlled by the central line 6 viewed from the slit. Typically, the centerline is designed with two peaks and troughs in the top view dimension, and its amplitude A x 0.3 times the thickness of the local leaf shape, ampl...

Embodiment 3

[0041] Please refer to Figure 2. A turbine blade trailing edge slit structure adopting wave-type ribs, comprising a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust slit channel 3 and a trailing edge slit rib 4;

[0042] The hollow turbine blade 1 is provided with a cold air channel 2 in the inner cavity, and a wave-shaped trailing edge exhaust slot 5 is opened along the chord direction at the trailing edge, and a plurality of wave-shaped trailing edge slots are evenly arranged inside it. The partition ribs 4 are arranged side by side to form discrete trailing edge exhaust slit channels 3 . Along the chord direction, the channel is in the shape of a wave with gradually attenuating amplitude and width, and its shape can be controlled by the central line 6 viewed from the slit. Typically, the centerline is designed with 8 peaks and troughs in the top view dimension, and its amplitude A x 0.1 times the thickness of the local airfoil, amplitude...

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Abstract

The invention belongs to the technical field of aero-engine turbine cooling, and relates to a turbine blade trailing edge slit cooling structure adopting wavy partition ribs. The trailing edge slit cooling structure comprises a hollow turbine blade, an inner cavity cool gas channel, trailing edge exhaust slit channels and the trailing edge slit partition ribs, wherein an inner cavity cool gas channel is formed inside the hollow turbine blade, a wavy trailing edge exhaust slit is formed in the trailing edge of the hollow turbine blade in the chordwise direction, the plurality of wavy trailing edge slit partition ribs are evenly arranged inside the wavy trailing edge exhaust slit, and are arranged side by side to form the discrete trailing edge exhaust slit channels so as to allow cool gas to be exhausted out of the blade. Through the structure of the trailing edge slit partition ribs, the structural strength of the trailing edge of the blade can be improved, the internal heat exchange area of the blade can be increased, and meanwhile, the cool gas in an inner cavity of the blade is guided, and the flowing direction of the cool gas is turned; and according to the trailing edge slit cooling structure, a cool gas flowing path is lengthened favorably, so that the cool gas is utilized more fully, the convective heat exchange area is increased, boundary layers are restrained, and theheat exchange effect is enhanced.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine cooling, and relates to a slit cooling structure at the trailing edge of a turbine blade using wave-type ribs. 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 ...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/187F01D5/188
Inventor 孔星傲吕东王楠李海旺周亦胄
Owner DALIAN UNIV OF TECH
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