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S-shaped fin structure suitable for cooling channel in rear edge of turbine blade

A turbine blade and internal cooling technology, which is applied in the direction of blade support elements, sustainable transportation, climate sustainability, etc., can solve the problems of complex cooling structure, high manufacturing cost, and difficult processing

Pending Publication Date: 2022-08-05
中科南京未来能源系统研究院
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, these cooling structures are relatively complex, the manufacturing cost is high, and some intermittent ribs still have structures such as filling sections, which makes processing too difficult

Method used

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  • S-shaped fin structure suitable for cooling channel in rear edge of turbine blade
  • S-shaped fin structure suitable for cooling channel in rear edge of turbine blade
  • S-shaped fin structure suitable for cooling channel in rear edge of turbine blade

Examples

Experimental program
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Effect test

Embodiment 1

[0026] combine Figure 4 , This embodiment provides an S-shaped fin structure applied to the cooling channel inside the trailing edge of the turbine blade, including the cooling channel and the S-shaped fin. Hydraulic diameter D of cooling channel h = 3mm, the S-shaped fins are composed of 7 arc fins and 6 straight fins arranged alternately in a row. The ratio of the fin height to the hydraulic diameter of the cooling channel is e / D h =0.05 (e=4mm), the width w of the rib is equal to the height e, and the ratio of the radius of the center line of the arc rib to the hydraulic diameter of the channel is r / D h = 0.25 (r=20mm), the ratio of the distance between adjacent arc ribs to the radius of the centerline of the arc rib k / r=2.5 (k=50mm), the radian of the centerline of the arc rib α=106.25°, and the length l=30mm. The S-shaped fins are arranged at equal intervals in the leaf height direction, the ratio of the rib spacing to the radius of the centerline of the arc rib is p / r...

Embodiment 2

[0028] combine Figure 5 , This embodiment provides an S-shaped fin structure applied to the cooling channel inside the trailing edge of the turbine blade, including the cooling channel and the S-shaped fin. Hydraulic diameter D of cooling channel h =3mm, the S-shaped fins are composed of 6 arc fins and 5 straight fins arranged alternately in a row, the ratio of the fin height to the hydraulic diameter of the cooling channel is e / D h =0.05 (e=4mm), the width w of the rib is equal to the height e, and the ratio of the radius of the center line of the arc rib to the hydraulic diameter of the channel is r / D h = 0.25 (r=20mm), the ratio of the distance between adjacent arc ribs to the radius of the centerline of the arc rib k / r=4 (k=80mm), the radian of the centerline of the arc rib α=60°, and the length l=69.28mm. The S-shaped fins are arranged at equal intervals in the leaf height direction, the ratio of the rib spacing to the radius of the centerline of the arc rib is p / r=1.0...

Embodiment 3

[0030] combine Image 6 , This embodiment provides an S-shaped fin structure applied to the cooling channel inside the trailing edge of the turbine blade, including the cooling channel and the S-shaped fin. Hydraulic diameter D of cooling channel h =3mm, the S-shaped fins are composed of 7 arc fins and 6 straight fins alternately arranged intermittently, the ratio of the fin height to the hydraulic diameter of the cooling channel is e / D h =0.05 (e=4mm), the width w of the rib is equal to the height e, and the ratio of the radius of the center line of the arc rib to the hydraulic diameter of the channel is r / D h = 0.25 (r=20mm), the ratio of the distance between adjacent arc ribs to the radius of the centerline of the arc rib k / r=2.5 (k=50mm), the radian of the centerline of the arc rib α=60°, and the length l=18mm. The S-shaped fins are arranged at equal intervals in the leaf height direction, the ratio of the rib spacing to the radius of the centerline of the arc rib is p / r=1...

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Abstract

The invention discloses an S-shaped fin structure suitable for a cooling channel in the rear edge of a turbine blade, and relates to the technical field of gas turbine cooling. The S-shaped fins are formed by alternately arranging arc ribs and straight ribs, the center lines of the arc ribs are arcs with the same radius, the circle centers are collinearly distributed, and the adjacent arc ribs are distributed in a central symmetry mode. The circle where the center line of the arc rib is located is tangent to the center line of the straight rib or the extension line of the straight rib. And the S-shaped fins are integrally arranged along the flow direction of cold air. The sections of the arc ribs and the straight ribs are rectangles with the same size, and no filling part exists. Compared with common cuboid fins (inclined ribs and crossed ribs), the arc rib structure can increase the convection heat exchange area, enhance the disturbance of airflow on the rear edge wall face and improve the heat exchange performance of the wall face, and the adjacent arc ribs are distributed in a central symmetry mode, so that the space distribution uniformity of the heat exchange performance of the wall face is improved.

Description

technical field [0001] The invention relates to the technical field of gas turbine cooling, in particular to an S-shaped fin structure applied to a cooling passage in a trailing edge of a turbine blade. Background technique [0002] Further increasing the inlet temperature of the gas turbine turbine is an effective way to improve the thermal performance of the gas turbine, but it also means that the turbine blades are subject to extremely high thermal loads, especially the leading edge, trailing edge and suction surface of the nozzle blades and turbine buckets Transition area. At present, the inlet temperature of advanced gas turbine turbines has far exceeded the temperature resistance limit of blade materials. Efficient turbine cooling technology is the key to ensuring the life of hot-end components and the stable operation of gas turbines. [0003] Turbine blades mostly use a composite cooling method combining internal and external. The interior of the blade is designed ...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/188Y02T50/60
Inventor 白林超施佳君彭姝璇
Owner 中科南京未来能源系统研究院
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