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A turbine blade branch network cooling structure

A technology for cooling structure and turbine blades, applied in the direction of supporting components of blades, machines/engines, mechanical equipment, etc., can solve the problems of small heat exchange area and cooling efficiency that cannot meet high thrust-to-weight ratio aeroengines, etc., to achieve increased cooling area, The effect of improving the heat exchange capacity

Active Publication Date: 2022-06-28
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the small heat exchange area of ​​this type of structure and less disturbance to the airflow, its cooling efficiency cannot meet the needs of high thrust-to-weight ratio aeroengines, and it is urgent to improve it.

Method used

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  • A turbine blade branch network cooling structure
  • A turbine blade branch network cooling structure
  • A turbine blade branch network cooling structure

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] figure 2 It is a schematic diagram of a turbine guide vane with a branch-net cooling structure provided by an embodiment of the present invention. As shown in the figure, the branch-net cooling structure of this embodiment is composed of two parts, a cylindrical support structure and a mesh connection structure. The cylindrical support structure in the branch-net cooling structure is perpendicular to the outer surface of the edge plate of the turbine guide vane, and the network connection structure is approximately parallel to the outer surface of the edge plate.

[0032] The cylindrical support structure in the branch network cooling structure is determined by the diameter φD 1 It is composed of cylinders with a length of = 1 mm, which are arranged in a regular triangle. Each cylinder is located at the vertex of the regular triangle, and the side length of the regular triangle is the distance between two adjacent cylinders L=3mm.

[0033] The network connection stru...

Embodiment 2

[0036] A turbine guide vane with a branch-mesh cooling structure, the cylindrical support structure in the branch-mesh cooling structure is defined by a diameter φD 1 It is composed of cylinders with a length of = 2mm, arranged in an equilateral triangle, and each cylinder is located at the apex of the equilateral triangle.

[0037] The network connection structure in the branch network cooling structure is determined by the diameter φD 2 = 2mm cylinder, the total height of the branch network cooling structure H = 3mm, the diameter of the gas film hole φd = 0.8mm, the angle between the axis of the gas film hole and the outer surface of the edge plate ∠A 2 =40°. The ratio of the diameter of the air film pores to the mesh connection is in the range of 0.8.

Embodiment 3

[0039] In the layout of the air film holes, a mode with less flow resistance can be adopted, that is, the cooling air inlet is arranged directly below the triangular mesh holes, such as Image 6 shown. Compared with the first embodiment, although this form reduces the distance of cooling air flow and reduces the cooling effect, it also reduces the flow resistance and loss, and also has the advantage of being easy to observe the blockage of the orifice. Therefore, the position of the air film holes can be reasonably arranged according to different working conditions and the cooling requirements of different positions of the edge plate under the condition that the size of the branch net structure remains unchanged, so as to maximize the utilization of the cooling gas.

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Abstract

The invention belongs to the technical field of aero-engine turbine blade cooling, and in particular relates to a turbine blade branch-net type cooling structure. The cylindrical support structure in the branch-network cooling structure is perpendicular to the outer surface of the turbine guide blade edge plate, and the mesh connection structure is approximately parallel to the outer surface of the edge plate. The cylindrical support structure in the branch network cooling structure is defined by the diameter φD 1 The cylinders are arranged in an equilateral triangle, each cylinder is located at the apex of the equilateral triangle, and the side length of the equilateral triangle is the distance L=3~5mm between two adjacent cylinders. Compared with the conventional cooling scheme, the present invention covers the outer surface of the edge plate, and can significantly increase the heat exchange area on the cold air side, enhance the degree of disturbance to the cooling air flow, and thus effectively improve the cooling effect. In addition, the structure can also enhance the deformation resistance of the flange and is easy to manufacture.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine blade cooling, and relates to a branch-net type cooling structure for turbine blades. Background technique [0002] Aeroengine is a power device that converts thermal energy into jet thrust or mechanical work. The higher the temperature before the turbine, the greater the thrust generated and the higher the engine performance. Data prediction shows that for every 100°C increase in the gas temperature before the turbine, the thermal efficiency of the engine increases by 8%, and the maximum thrust can be increased by about 15%. Therefore, increasing the gas temperature has become the primary pursuit of the design. Under such conditions, the temperature resistance of the turbine blade, which is a typical hot end component, has become a bottleneck factor restricting the improvement of aero-engine performance. Under the circumstance that it is difficult to further improve the high tempera...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/187
Inventor 吕东康浩梁彩云苏航王楠孙一楠
Owner DALIAN UNIV OF TECH
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