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Interrupted groove blade top structure with transverse seam holes for turbine blade

A technology of turbine blades and transverse slits, which is applied to the supporting elements of blades, machines/engines, and engine functions, etc., can solve the problems of complex leakage flow flow structure, reduced blade service life, and easy ablation of moving blade tips. Improve film cooling efficiency, reduce heat transfer intensity, and reduce the effect of intensity

Pending Publication Date: 2021-01-19
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Affected by the gap leakage flow, the heat transfer coefficient of the top area of ​​the turbine power blade is extremely high, which makes the blade top vulnerable to thermal corrosion of high-temperature gas and reduces the service life of the blade
The leakage flow in the gap has a complex flow structure and uneven heat transfer, so the tip of the moving blade is easily ablated, and then ruptures and fails

Method used

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  • Interrupted groove blade top structure with transverse seam holes for turbine blade
  • Interrupted groove blade top structure with transverse seam holes for turbine blade
  • Interrupted groove blade top structure with transverse seam holes for turbine blade

Examples

Experimental program
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Effect test

Embodiment 1

[0026] This embodiment is a discontinuous groove tip structure with transverse slots, by arranging the suction side side groove wall 3 and the pressure side side groove wall 4 on the blade tip 1, and arranging transverse slits at the fracture groove wall. For hole 2, the discontinuity of the discontinuous groove is located on the pressure side, and the discontinuity start position is located at the stagnation point of the leading edge. The groove wall 3 on the suction side and the groove wall 4 on the pressure side have the same groove height, and the centerline G of the transverse slot hole is parallel to the arc of the pressure surface.

[0027] The groove height of the groove wall 3 on the suction side is J, which is 1.4mm. The groove height K of the groove wall 4 on the pressure side is 1.4 mm. The chord length at blade top 1 is C, and the value is 40mm. The length at the wall of the fracture groove is A, and the value is 0.3C. The slit width of the transverse slit 2 is...

Embodiment 2

[0030] This embodiment is a discontinuous groove tip structure with transverse slots, by arranging the suction side side groove wall 3 and the pressure side side groove wall 4 on the blade tip 1, and arranging transverse slits at the fracture groove wall. For hole 2, the discontinuity of the discontinuous groove is located on the pressure side, and the discontinuity start position is located at the stagnation point of the leading edge. The groove wall 3 on the suction side and the groove wall 4 on the pressure side have the same groove height, and the center line G of the transverse slot hole is parallel to the arc of the pressure surface.

[0031]The groove height of the groove wall 3 on the suction side is J, which is 1.0mm. The groove height of the groove wall 4 on the pressure side is K, which is 1.0mm. The chord length at blade tip 1 is C, and the value is 40mm. The length at the wall of the fracture groove is A, and the value is 0.5C. The slit width of the transverse ...

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Abstract

The invention discloses an interrupted groove blade top structure with transverse seam holes for a turbine blade. The structure is characterized in that a suction surface side groove wall and a pressure surface side groove wall are arranged on a blade top, the transverse seam holes are formed in the broken groove wall, the interrupted part of an interrupted groove is positioned on the pressure surface side, and the interrupted starting position is positioned at a front edge stationary point. By eliminating a gas reattachment area formed in the groove blade top in the interrupted area, the heatexchange coefficient of the front edge area of the blade top is effectively reduced, the local heat exchange strength is weakened, and the cooling characteristic of the blade top is improved. The transverse width of the groove can be controlled through the reasonable length of the pressure surface side groove wall, so that only one backflow vortex is formed in the groove after fuel gas enters thegroove, and the gas reattachment area in the groove is eliminated; and the transverse seam holes can effectively improve the transverse coverage area after jet flow outflow, the local air film cooling efficiency of the blade top is improved, the working efficiency of the turbine power blade is effectively improved, and the overall performance of an aero-engine is improved.

Description

technical field [0001] The invention relates to the technical field of cooling the turbine blades of gas turbines, in particular to an intermittent groove tip structure with transverse slot holes for the turbine blades. [0002] technical background [0003] With the improvement of gas turbine performance, the turbine inlet temperature continues to increase, and 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 gas from the wall and realize the cooling protection effect on the heated wall. [0004] Cylindrical air film holes are the earliest air film hole type. A large number of scholars at home and a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18F01D5/14
CPCF01D5/186F01D5/147F05D2260/221
Inventor 朱惠人张博伦姚春意刘存良张丽郭涛许卫疆
Owner NORTHWESTERN POLYTECHNICAL UNIV
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