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Turbine blade bent branch net type cooling structure

A technology for cooling structure and turbine blades, which is applied in the direction of blade support components, engine components, machines/engines, etc., which can solve the problems of small heat transfer 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: 2021-06-08
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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  • Turbine blade bent branch net type cooling structure
  • Turbine blade bent branch net type cooling structure
  • Turbine blade bent branch net type cooling structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

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

[0032] The cylindrical support structure in the curved branch cooling structure is defined by the diameter φD 1 The cylinders of =1 mm are arranged in an equilateral triangle, each cylinder is located at the vertices of the equilateral triangle, and the side length of the equilateral triangle is the distance L=3mm between two adjacent cylinders.

[0033] The curved network connection structure in the curved branch network cooling structure along the axis diameter φD 2 =1mm,...

Embodiment 2

[0036] The utility model relates to a turbine guide vane with a curved branch-network cooling structure, in which the cylindrical support structure is perpendicular to the outer surface of the edge plate of the turbine guide vane.

[0037] The cylindrical support structure in the curved branch cooling structure is defined by the diameter φD 1 = 2mm cylinders, arranged in a regular triangle, each cylinder is located at the apex of the regular triangle, the typical value of the side length of the regular triangle, that is, the distance L between two adjacent cylinders, is 4mm.

[0038] The curved network connection structure in the curved branch network cooling structure along the axis diameter φD 2 = 1-2 mm, the axis of the elliptical curved network connection structure is elliptical, the length of the major axis of the ellipse is L, and the length of the minor axis is 0.7L, with a typical value of 0.5L. The total height of the curved branch network cooling structure is H = 4m...

Embodiment 3

[0040] Considering that the structure will be applied in different working conditions, the working temperature is different, and the thermal expansion coefficient of the material is different, so two kinds of curved branch network cooling structures are provided. figure 2 It is an elliptical curved branch network cooling structure, Figure 6 It is a circular curved branch network cooling structure.

[0041] The circular curved branch network cooling structure is the case where the long and short axes of the ellipse are the same. In this structure, the branches connected between two adjacent cylindrical supports are all semicircular, and the axis is a semicircle with a radius of 0.5L. The cross-sections in each direction are typical values ​​φD 2 = 1 mm circle. This structure takes into account the large difference in thermal expansion between the edge plate and the curved mesh connection structure in a high-temperature environment. The edge plate is directly in contact with...

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Abstract

The invention belongs to the technical field of aero-engine turbine blade cooling, and relates to a turbine blade bent branch net type cooling structure. The turbine blade bent branch net type cooling structure comprises an array cylindrical supporting structure perpendicular to the outer surface of a marginal plate and a bent net-like connecting structure. The section of the cylindrical supporting structure is in the shape of a circle with the diameter phi D<1> of 1-2mm, more turbulent flow structures can be arranged in a narrow space, all cylinders are arranged in a regular triangle around an inlet of a cooling air channel of a blade inner cavity on the outer surface of the marginal plate, all the cylinders are located at vertexes of the regular triangle respectively, and the side length of the regular triangle, namely the distance L between adjacent cylindrical supports, is 3-5mm. The structure covers the outer surface of the marginal plate, the heat exchange area on the cold air side can be remarkably enlarged, the disturbance degree of cooling airflow is enhanced, and therefore the cooling effect is effectively improved. In addition, the structure can enhance the anti-deformation capacity of the marginal plate 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 curved branch net type cooling structure of a turbine blade. Background technique [0002] An aero engine is a power device that converts thermal energy into jet thrust or mechanical work. The higher the temperature in front of the turbine, the greater the thrust and the higher the engine performance. Data predictions show that for every 100°C increase in the gas temperature in front of the turbine, the thermal efficiency of the engine will increase by 8%, and the maximum thrust will increase 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, becomes the bottleneck factor restricting the performance improvement of the aero-engine. In the case that it is difficult to further improve the high tem...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/187
Inventor 吕东王相平康浩陈云王楠孙一楠
Owner DALIAN UNIV OF TECH
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