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Arched groove gas film cooling structure for turbine blades

A technology of turbine blade and air film cooling, applied in the direction of blade support elements, engine elements, machines/engines, etc., can solve the problems of increased flow resistance, limited jet flow, momentum loss, etc., to reduce flow resistance and momentum loss. , Increase the effect of span direction coverage

Inactive Publication Date: 2017-04-26
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in subsequent studies, it was found that the gas film formed by the cylindrical hole could not provide cooling protection for the area between the holes, and the jet gas was raised so that the gas film covering the near wall could not be formed.
With the development of film cooling technology, it is found that opening a transverse groove with a certain depth and width at the exit of the film hole along the direction perpendicular to the flow of cold air can significantly improve the cooling effect of the cooling wall surface downstream of the groove, but in the case of the film hole The trailing edge of the groove at the exit has a strong blocking effect on the jet flow. It is difficult for the jet flow to spread to both sides, and a backflow vortex will be formed in the groove, which greatly increases the flow resistance. The jet flow between the holes is very limited and cannot form a uniform flow. The air film is covered by the air film, and after the jet leaves the air film hole, a large amount of jet flow is injected into the main flow due to the high normal velocity, the air film cannot be formed near the wall, and the cooling effect is not ideal. Edge trailing edge structure to improve film cooling effect
A structure similar to slot air film holes has also been proposed, but due to the slope-shaped front and rear edges of the groove, the jet flow cannot achieve a smooth transition, resulting in momentum loss, and the normal phase velocity of the jet flow has not been significantly improved.
Moreover, Jiang Yongjian and others found that changing the trailing edge of the groove to a slope shape can improve the span-wise coverage of the jet, but the improvement of cooling efficiency is not obvious
As a result, the reduction of the normal phase velocity and the improvement of the spanwise diffusion ability of the jet are limited.

Method used

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  • Arched groove gas film cooling structure for turbine blades
  • Arched groove gas film cooling structure for turbine blades
  • Arched groove gas film cooling structure for turbine blades

Examples

Experimental program
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Embodiment 1

[0030] This embodiment is an arched groove air film cooling structure on the turbine rotor blade. The air film holes 7 with arched grooves are arranged on the pressure surface of the turbine blade, and the air film holes 8 with arched grooves are arranged on the suction surface, and the air is supplied by the inner cooling channel 9; the air film holes located on the air film orifice plate 2 3. The front edge 1 of the arched groove and the rear edge 4 of the groove with rounded corners are provided at the outlet. The combination of the front edge 1 of the arched groove and the rear edge 4 of the groove with rounded corners forms the arched groove.

[0031] Among them, the air film hole 3 diameter D f is 0.5mm, and the flow angle θ is 30°. The thickness H of the arched groove leading edge 1 and the groove trailing edge 4 with rounded corners is 1D f , whose value is 0.5mm. The arched groove leading edge 1 is obtained by taking the difference between the bottom of the transve...

Embodiment 2

[0034] This embodiment is an arched groove air film cooling structure applied to a turbine rotor blade. Air film holes 7 with arched grooves are set on the pressure surface of the turbine blades, and air film holes 8 with arched grooves are set on the suction surface of the turbine blades, and the air is supplied by the internal cooling passage 9; on the air film orifice plate 2 The outlet of the air film hole 3 is provided with an arched groove front edge 1 and a groove rear edge 4 with rounded corners, and the combination of the arched groove front edge 1 and the groove rear edge 4 with rounded corners forms an arched groove . Wherein the bottom of the front edge 1 of the arched groove is flush with the front edge of the outlet of the gas film hole 3, and the trailing edge 4 of the groove with rounded corners is flush with the rear edge of the outlet of the gas film hole 3.

[0035] In the structure of this embodiment, the diameter of the gas film hole 3 is D f is 0.5mm, a...

Embodiment 3

[0038] This embodiment is an arched groove air film cooling structure on the turbine rotor blade. The air film holes 7 with arched grooves are arranged on the pressure surface of the turbine blade, and the air film holes 8 with arched grooves are arranged on the suction surface, and the air is supplied by the internal cooling passage 9. It is characterized in that: it is located on the air film orifice plate 2 The air film hole 10 outlet is provided with an arched groove front edge 1 and a groove rear edge 4 with rounded corners, and the combination of the arched groove front edge 1 and the groove rear edge 4 with rounded corners forms an arched groove. Among them, the minimum cross-sectional equivalent diameter D of the gas film hole 10 f is 1mm, and the flow angle θ is 30°. The thickness H of the arched groove leading edge 1 and the groove trailing edge 4 with rounded corners is 1.2D f , its value is 1.2mm. The arched groove leading edge 1 is obtained by taking the diffe...

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Abstract

The invention discloses an arched groove gas film cooling structure for turbine blades. An arched groove front edge and a rounded groove back edge are arranged at an outlet of a gas film hole, and the structure is formed. The arched groove front edge is obtained through differencing of the bottom of a transverse groove and a quarter of a cylinder arc, and the radius of the cylinder arc is smaller than the groove depth. Smooth transition from the normal velocity of gas flow after the gas flow leaves the gas film hole to the flow-direction velocity is realized effectively by the aid of the arched front edge, and the cold gas loss caused by direct injection of a large quantity of cooling gas flow into a main flow is avoided; and the momentum loss of jet flow is reduced through smooth transition of the velocity of the cooling gas flow, so that the jet flow is better attached to the wall surface. Collisions between the jet flow and the back edge are reduced by the aid of the rounded groove back edge, so that the flow resistance of the cooling gas flow is reduced, the jet flow is divided to two sides more easily, the spanwise covering of the cold gas is increased, meanwhile, the cold gas climbing out of the groove can be closely attached to the position close to the wall surface, protection of the gas film on the downstream wall surface of the groove is formed, and the cooling effect is good.

Description

technical field [0001] The invention relates to the technical field of cooling the turbine blades of gas turbines, in particular to an arched groove air film cooling structure for the turbine blades. [0002] technical background [0003] With the improvement of gas turbine performance, the turbine inlet temperature continues to increase. Nowadays, the inlet temperature of some advanced engines has reached more than 2000K. Therefore, effective cooling measures must be used to protect the turbine blades to avoid high temperature corrosion and damage to the blades. Film cooling is one of the typical cooling methods used on blades. Air film cooling is to inject a low-temperature airflow along the tangent or at a certain angle near the wall to isolate the high-temperature combustion body from the wall to achieve cooling protection for the heated wall. [0004] As the earliest hole type, air film cylindrical hole type has been widely used and studied. However, in subsequent stud...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 张丽张博伦朱惠人刘存良魏建生姚春意
Owner NORTHWESTERN POLYTECHNICAL UNIV
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