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Turbine blade adopting chordwise rotary cooling channel

A technology for turbine blades and cooling passages, applied in the direction of blade support elements, machines/engines, mechanical equipment, etc., can solve the problems of short flow distance, low cooling effect, small heat transfer area of ​​cold air and trailing edge, etc., to increase The ability to heat, improve the cooling effect, and avoid the effect of excessive temperature rise

Active Publication Date: 2021-06-04
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This type of trailing edge split cooling structure only relies on the ribs on the trailing edge to disturb the cold air, the heat exchange area between the cold air and the trailing edge is small, the flow distance is short, and the cooling effect is low

Method used

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  • Turbine blade adopting chordwise rotary cooling channel
  • Turbine blade adopting chordwise rotary cooling channel
  • Turbine blade adopting chordwise rotary cooling channel

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] A turbine blade using a chord-direction rotary cooling channel is mainly composed of a gas collection cavity 5, a rotary cavity 6, and an exhaust cavity 7, such as figure 2 shown.

[0028] The hollow turbine blade 1 with a chord length L=40 mm is provided with an inner cavity cold air passage 2 for low-temperature cooling gas to flow inside the blade to cool the blade. The air collection chamber 5 guides the cold air from the blade root into the interior of the blade, flows downstream into the swivel chamber 6, and the length of the swirl chamber is L 1 = 6mm. The cold air makes two 180° turns in the cavity along the chord direction from the blade back to the blade pot. The cavity is composed of an L-shaped partition wall 10 on the side of the basin, an L-shaped partition wall 11 on the back side, and circular spoiler columns 8 staggeredly combined. The short side of the basin side L-shaped partition wall 10 is vertically connected with the leaf basin, and its lengt...

Embodiment 2

[0030] A turbine blade using a chord-direction rotary cooling channel is mainly composed of a gas collection cavity 5, a rotary cavity 6, and an exhaust cavity 7, such as Figure 4 shown

[0031] The hollow turbine blade 1 with a chord length L=40 mm is provided with an inner cavity cold air passage 2 for low-temperature cooling gas to flow inside the blade to cool the blade. The air collection chamber 5 guides the cold air from the root of the blade into the interior of the blade, flows downstream and enters the rotary chamber, and its length is L 1 = 6 mm. The cold air makes two 180° turns along the chord direction from the blade pot to the blade back in the cavity. The cavity is composed of an L-shaped partition wall 10 on the side of the basin, an L-shaped partition wall 11 on the back side, and circular spoiler columns 8 staggeredly combined. The short side of the basin side L-shaped partition wall 10 is vertically connected with the leaf basin, and its length l 1 = 2...

Embodiment 3

[0033] As shown in Fig. 5(a), a turbine blade with chordwise rotating cooling channels is used on both the leading edge and the trailing edge. The structure of the leading edge of the blade is similar to that of the trailing edge, and is also composed of an air collecting chamber 5, a rotary chamber 6 and an exhaust chamber 7. The front exhaust cavity is composed of an L-shaped partition wall 23 on the side of the front edge basin, an L-shaped partition wall 24 on the back side of the front edge, and circular spoiler columns 8 staggeredly combined. The short side of the L-shaped partition wall 23 on the side of the front edge basin is vertically connected to the leaf basin, and the short side of the L-shaped partition wall 24 on the back side of the front edge is vertically connected to the leaf back. The cold air makes two 180° turns along the chord direction from the back of the blade to the blade pot in the leading edge and then is discharged from the air film hole on the l...

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Abstract

The invention belongs to the technical field of aero-engine turbine cooling, and relates to a turbine blade adopting a chordwise rotary cooling channel. In a conventional tail edge crack structure, cold air flows into the blade from the blade root and is directly exhausted after flowing through a tail edge partition rib. Heat exchange between cold air and the blade mainly occurs on a blade basin, a blade back and the tail edge partition rib, and the heat exchange area is limited. In the blade, the cold air flows through the chordwise rotary cooling channel, heat exchange between the cold air and two L-shaped partition walls and a circular turbulent flow column is increased, and compared with a conventional structure, the heat exchange area is increased by about 20%. More heat exchange areas increase the capacity of taking away heat of the blade, and the cooling effect of the blade is improved.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine cooling, and relates to a turbine blade adopting a chord-direction rotary cooling channel. 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 air inside the blades, and the air film is formed to cover and isolate the gas heating when the blades are discharged, which is the main solution to the cooling problem of the turbine blades. At the same time, the blades have "larger internal heat transfer area", "smaller cold air flow resistance", "higher heat transf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/188
Inventor 吕东李泳凡刘英实庞清楠孔星傲孙一楠
Owner DALIAN UNIV OF TECH
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