Composite blade top groove structure capable of improving turbine gas-heat performance

Abstract

The invention discloses a composite blade top groove structure capable of improving turbine gas-heat performance, and belongs to the field of gas turbines. A composite blade top groove comprises a conventional blade top groove and a blade top groove shoulder wall, wherein the blade top groove shoulder wall is arranged in the circumferential direction of the top of a blade; longitudinal fins, transverse cut-off fins and grid-shaped fins are arranged in the conventional blade top groove to form the composite blade top groove; the three kinds of fins are perpendicular to the groove bottom surface fixed to the composite blade top groove; the longitudinal fins are arranged along the blade top mean camber line; the four transverse cut-off fins are arranged in the direction perpendicular to the blade top mean camber line, the blade top mean camber line is equally divided into five sections, and the first transverse cut-off fin, the second transverse cut-off fin, the third transverse cut-off fin and the fourth transverse cut-off fin are sequentially arranged from the front edge to the tail edge; and the grid-shaped fins are arranged in a front edge high-heat load area of the composite blade top groove and used for blocking scouring of blade top front edge leakage flow to the bottom surface of the groove. According to the blade top groove structure, the heat load of the surface of a blade top can be obviously reduced, and safe and efficient operation of a high-pressure gas turbine is guaranteed.

Description

technical field [0001] The invention belongs to the field of gas turbines, and in particular relates to a composite blade top groove structure with improved gas-thermal performance of the turbine. Background technique [0002] With the increasingly prominent environmental problems and the adjustment of energy structure, gas turbines are widely used in power generation, aerospace industry, chemical industry and mechanical power fields as thermal power conversion equipment with high thermal efficiency. At present, increasing the gas temperature at the inlet of the gas turbine is one of the most direct and effective methods to improve the power and thermal efficiency of the gas turbine. The low-aspect-ratio high-pressure rotor blades of gas turbines in actual service are all designed without shrouds, which directly leads to a significant increase in the leakage flow loss in the top clearance of the high-pressure turbine stage rotor blades and the heat load on the blade tip. Th...

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Problems solved by technology

[0005] like image 3 As shown, the prior art 202011126947.9 is a discontinuous groove tip structure for turbine blades with transverse slots, by arranging the suction surface side groove wall and the pressure surface side groove wall on the blade tip, and breaking the groove The wall is arranged with transverse slots. The advantage of this structure is that the discontinuous grooved tip can effectively reduce the heat transfer coefficient of the leading edge area of ​​the blade tip by eliminating the gas reattachment area formed in the grooved tip in the discontinuous area, weakening the The strength of the local heat exchange improves the cooling characteristics of the blade tip; however, it cannot effectively weaken the leakage of the blade tip clearance, so that the chamber vortex in the groove cannot be maintained, so the strip-shaped high heat exchange area on the bottom surface of the groove cannot be eliminated

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