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Cross type Y air film hole cooling structure for turbine blade

A technology of turbine blades and air film holes, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve problems such as increasing aerodynamic losses, and achieve the effects of reducing aerodynamic losses, easy processing, and uniform air output.

Inactive Publication Date: 2019-05-10
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is worth noting that the shaped holes provide high cooling efficiency while also increasing aerodynamic losses

Method used

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  • Cross type Y air film hole cooling structure for turbine blade
  • Cross type Y air film hole cooling structure for turbine blade
  • Cross type Y air film hole cooling structure for turbine blade

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] In this embodiment, the pressure surface cross-shaped Y air film hole 9 and the pressure surface cross-shaped Y air film hole 12 are arranged on the pressure surface of the turbine blade, and the air is supplied by the internal cooling passage 8 and the internal cooling passage 10. The cross-shaped Y air film holes 11 on the suction surface are arranged, and the air is supplied by the inner cooling channel 10 . Among them, the first cylindrical air film hole 4 and the second cylindrical air film hole 13 cross through and stretch their interface to form the upstream Y air film hole 3; the third cylindrical air film hole 7 and the fourth cylindrical air film hole 14 cross through And stretch the junction surface to form the downstream Y air film hole 6, and the upstream Y air film hole 3 and the downstream Y air film hole 6 are combined in cross rows to form a cross-shaped Y air film hole cooling structure.

[0028] In this embodiment, the minimum cross-sectional equivale...

Embodiment 2

[0031] In this embodiment, the cross-shaped Y air film holes 9 and cross-shaped Y air film holes 12 are arranged on the pressure surface of the turbine blade, and the air is supplied by the internal cooling channel 8 and the internal cooling channel 10, and the cross-shaped Y air film hole is arranged on the suction surface of the turbine blade. The air film holes 11 are supplied with air from the internal cooling channel 10 . Among them, the first cylindrical air film hole 4 and the second cylindrical air film hole 13 cross through and stretch their interface to form the upstream Y air film hole 3; the third cylindrical air film hole 7 and the fourth cylindrical air film hole 14 cross through And stretch the junction surface to form the downstream Y air film hole 6; the upstream Y air film hole 3 and the downstream Y air film hole 6 are combined in cross rows to form a cross-shaped Y air film hole cooling structure.

[0032] In this embodiment, the minimum cross-sectional equ...

Embodiment 3

[0035] In this embodiment, the cross-shaped Y air film holes 9 and cross-shaped Y air film holes 12 are arranged on the pressure surface of the turbine blade, and the air is supplied by the internal cooling channel 8 and the internal cooling channel 10, and the cross-shaped Y air film hole is arranged on the suction surface of the turbine blade. The air film hole 11 is supplied by the internal cooling channel 10, wherein the first cylindrical air film hole 4 and the second cylindrical air film hole 13 intersect and penetrate and stretch their interface to form the upstream Y air film hole 3; the third cylindrical air film hole 3 The film hole 7 and the fourth cylindrical air film hole 14 intersect and stretch their interface to form the downstream Y air film hole 6; the upstream Y air film hole 3 and the downstream Y air film hole 6 are combined to form a cross-shaped Y air film hole cooling structure.

[0036] In this embodiment, the minimum cross-sectional equivalent diamete...

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Abstract

The invention discloses a cross type Y air film hole cooling structure for a turbine blade. Two rows of air film holes are formed in an air film hole plate in the flow direction, and the air film holes are distributed in a cross mode. Each Y air film hole is formed by crossing two cylindrical air film holes and extending the connected face, wherein the outlets of the two cylindrical air film holesboth have the certain inclination angle in the extending direction. By means of the cross type Y air film hole cooling structure, jet flow is more easily divided to two sides, the jet flow extendingdirection coverage is increased, and jet flow pneumatic loss is reduced. By means of mutual action of the front and rear rows of Y air film holes, an inner volume vortex is formed on the downstream ofthe air film holes, old air leaving from the Y air film holes is tightly attached to the near wall face position, and the downstream wall faces of the air film holes are effectively protected. Each Yair film hole is provided with an air film hole inlet, the channel middle section is divided into two paths of cold air, the air output of two outlets of each Y air film hole is more uniform, and theY air film holes have the advantages of being simple in structure, easy to machine and good in air film covering effect.

Description

technical field [0001] The invention relates to the technical field of cooling of turbine blades of gas turbines, in particular to a cross-shaped Y-film hole cooling structure for turbine blades. technical background [0002] Since its inception, gas turbines have been widely used in industry after decades of development. In industrial applications, designers have gradually increased the temperature before the turbine according to the principle of engineering thermodynamic cycle, which has effectively improved the performance of the gas turbine. However, limited by the heat resistance of the turbine blade material, the temperature in front of the turbine has reached a bottleneck. Therefore, effective cooling of the turbine blades is required to ensure the safe and efficient operation of the gas turbine. As an external cooling method, film cooling is widely used in the cooling design of turbine blades. The basic principle of air film cooling: open slots or small holes on hi...

Claims

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Application Information

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IPC IPC(8): F01D5/18
Inventor 朱惠人姚春意张博伦魏建生付仲议
Owner NORTHWESTERN POLYTECHNICAL UNIV
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