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Turbine blade round hole air film cooling structure with strip slit opening

A technology of turbine blade and air film cooling, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve problems such as convenient processing and complicated processing, improve air film cooling efficiency, eliminate reverse vortex pairs, and reduce outlet effect of speed

Inactive Publication Date: 2014-04-02
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In contrast, fan-shaped holes and contraction and expansion holes can greatly improve the cooling efficiency, but because the diameter of the air film hole is too small, the convenient processing is relatively complicated

Method used

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  • Turbine blade round hole air film cooling structure with strip slit opening
  • Turbine blade round hole air film cooling structure with strip slit opening
  • Turbine blade round hole air film cooling structure with strip slit opening

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] Since the structures on multiple air-porous films are symmetrical, only a single air-film pore structure is selected for illustration in this embodiment.

[0025] Please combine image 3 and Figure 5 , the angle of the circular air film hole is α, and the range is between 20° and 90°. The length of the gas film hole is generally 4 to 6D (D is the diameter of the gas film hole), and the distance between the gas film holes is generally 3D. The overall size of the slit outlet 6 is W×H, W is the overall width of the slit outlet 6, along the direction of fluid flow; H is the height of the slit outlet 6, along the height direction of the air film hole. 2D is recommended for W size, and 1~2D is recommended for H size. The recommended angle between the angle β of the slit plate 4 and the fluid flow direction is 30° to 150°.

[0026] In this example, the diameter D of a single air film hole is 12.7mm, the dimension W×H of the transverse groove is 25.4×6.35mm, and the angle ...

Embodiment 2

[0028] Please combine Figure 4 and Figure 6 , The included angle between the angle β of the slit plate and the direction of fluid flow is 30° to 150°. All the other are with embodiment 1.

[0029] Figure 7 Shown are the cooling efficiency contours of different air film hole structures. As can be seen from the figure, the spanwise coverage area of ​​known air film holes and air film holes with transverse grooves is substantially the same, and the air film holes with vertical slit outlets and 30-degree inclined slit outlets of the present invention make air Membrane pores downstream are fully covered. Compared with known air film holes and air film holes with transverse grooves, the air film hole structure with slit outlets in the present invention can better protect the blade surface.

[0030] Figure 8 Shown is the spanwise average film cooling efficiency downstream of the film hole. It can be seen from the figure that the air film hole with 30-degree inclined slit e...

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Abstract

The invention relates to a turbine blade round hole air film cooling structure with a strip slit opening. The strip slit opening is arranged at the position of an air film hole outlet and along the high direction of a blade and comprises at least one slit plate which partitions the air film hole outlet into two slits. The well-known air film cooling outlet structure is changed into the trip slit opening structure, speed of cooling working medium at the outlet is reduced, reverse vortex pairs caused by high-speed cooling working medium are eliminated, and therefore, air film cooling efficiency is increased. The turbine blade round hole air film cooling structure with the strip slit opening is simple and easy to manufacture.

Description

technical field [0001] The invention is proposed for the external cooling technology of the turbine blades of the gas turbine, and is used for being arranged on the turbine blades to realize effective cooling of the blades. More specifically, it relates to a turbine blade circular hole air film cooling structure with slit outlets. Background technique [0002] As a commonly used and important external cooling method for turbine blades, air film cooling introduces cooling air by opening film holes and covers the surface of high-temperature turbine blades, forming a cold air film to separate high-temperature gas from the surface of turbine blades. At present, the focus of research is mainly on the structure of gas film pores. figure 1 and figure 2 There are two kinds of gas film hole structures known at present. [0003] figure 1 As shown in the air film hole, due to the fast fluid velocity at the exit of the air film hole, reverse vortex pairs will be generated, causing ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 成克用淮秀兰
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI