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Combined structure air film hole for cooling front edge of turbine blade

A combined structure and technology of turbine blades, applied in the direction of supporting elements of blades, engine elements, machines/engines, etc., can solve the problems of small diameter, difficult to make air film holes in rectangular structure, unsuitable blade leading edge, etc.

Inactive Publication Date: 2021-06-08
成都中科翼能科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because of the large surface curvature and small diameter of the leading edge area of ​​the blade, it is difficult to make air film holes with a rectangular structure. In addition, the rectangular holes are prone to stress concentration, which is not suitable for the leading edge of the blade, especially for the air film hole at the leading edge of the rotor blade. film cooling

Method used

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  • Combined structure air film hole for cooling front edge of turbine blade
  • Combined structure air film hole for cooling front edge of turbine blade

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0019] Such as figure 1 and figure 2 As shown, in order to improve the effect of air film cooling on the leading edge of the turbine rotor blade and solve the problem of air film cooling in the cylindrical air film holes on the leading edge of the blade, this embodiment provides a combined structure air film for cooling the leading edge of the turbine blade Holes, including the first through hole 1 and the tapered hole 2 connected in sequence from the inlet direction to the outlet direction, the first through hole 1 and the tapered hole 2 are combined into a combined structure air film hole, which runs through the leading edge of the turbine blade 3, wherein, The first through hole 1 is non-coaxially arranged with the tapered hole 2, which can form a better cooling air film at the leading edge of the turbine blade 3, significantly improve the cooling effect of the turbine blade 3, reduce the temperature of the wall surface of the turbine blade 3 leading edge, and The cross-s...

Embodiment 2

[0024] This embodiment is a further improvement made on the basis of Embodiment 1. The specific differences between this embodiment and Embodiment 1 are:

[0025]As a specific embodiment, it needs to be further explained in this embodiment that the taper angle of the tapered hole 2 is not less than 10°, specifically it can be 10°, 30°, 50°, 70°, 80° or 110° and so on, because the cone angle of the tapered hole 2 is less than 120°, so as long as the cone angle of the tapered hole 2 is greater than or equal to 10° and less than 120°, it can be determined according to the actual situation. Without specific limitation, the diameter of the air outlet can be increased within the same length to meet the requirement that the diameter of the air outlet of the tapered hole 2 is larger than the diameter of the first through hole 1, thereby forming a better cooling air film at the leading edge of the blade. Significantly improve the cooling effect of the blade and reduce the wall temperat...

Embodiment 3

[0027] This embodiment is a further improvement made on the basis of Embodiment 1. The specific differences between this embodiment and Embodiment 1 are:

[0028] As a specific implementation, what needs to be further explained in this implementation is that the difference from the first embodiment is that the cross section of the tapered hole 2 is an elliptical structure. The tapered hole 2 of the elliptical structure is also convenient to process, and the inner wall surface does not have any angular structure. When the cold air enters the tapered hole 2 of the elliptical structure, no additional stress will be generated, and the tapered hole 2 of the elliptical structure The end with a larger aperture is used as its gas outlet, and the end with a smaller aperture is used as its inlet. The inlet of the elliptical tapered hole 2 is connected with the outlet of the first through hole 1, ensuring gas stability. On the basis of the circulation and the enlargement of the air outle...

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Abstract

The invention discloses a combined structure air film hole for cooling the front edge of a turbine blade. The air film hole comprises a first through hole and a conical hole which are communicated in sequence from the inlet direction to the outlet direction, the first through hole and the conical hole are arranged in a non-coaxial manner, and the cross section area of an outlet of the conical hole is larger than the area of the cross section of the first through hole; the axis of the first through hole is a straight line; and the inner wall surface of the first through hole and the inner wall surface of the conical hole have no corner angles. According to the combined structure air film hole, a well cooling air film can be formed at the front edge of the blade, the first through hole controls the flow of cooling air, the conical hole increases the outlet area of the air film hole, the speed of cooling air at the outlet of the air film hole is reduced, the covering effect of cooling air flow is improved, the cooling effect of the blade is remarkably improved, and the wall surface temperature of the front edge of the blade is reduced; and the sharp edge of the outlet edge of the air film hole is passivated, a stress concentration coefficient of the outlet edge of the air film hole is improved, the stress of the outlet edge of the air film hole is reduced, the wall surface temperature of the blade is reduced, the reliability of the blade is improved and the service life of the blade is prolonged.

Description

technical field [0001] The invention belongs to the technical field of gas turbines and aero-engines, and in particular relates to a combined structure air film hole used for cooling the leading edge of a turbine blade. Background technique [0002] In high-performance gas turbines, the gas temperature before the turbine is much higher than the temperature of the material used in the turbine blades, especially the gas temperature felt by the leading edge of the turbine blade is the highest. film cooling. In order to ensure that the cooling air at the leading edge of the blade can be discharged through the air film hole in all states, a higher cold air pressure margin is usually selected, but the pressure of the cold air discharged from the air film hole needs to match the gas pressure on the outer surface of the blade. If it is too low, the cold air may not be discharged from the air film hole, and even gas will enter the blade, and the blade will ablate and fail in a short...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 徐世辉蔡鹏王海林周江锋方圆杜治能
Owner 成都中科翼能科技有限公司
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