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Device for cooling guiding device group of turbine

A technology for cooling turbines and guides. It is used in the cooling of engines, cooling of turbines/propulsion devices, and engine components. It can solve the problems of blades affecting service performance and service life, and achieve the purpose of relieving cracks and improving performance and service life. Effect

Active Publication Date: 2015-02-11
HUNAN HANGXIANG GAS TURBINE
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a device for the turbine guider group of a gas turbine, so as to solve the problem that the existing device does not connect the flow passage surfaces of the inner and outer edge plates of the guide vane assembly itself and the airfoil and the flow passage surfaces of the inner and outer edge plates All-round cooling at all places leads to the technical problem of cracks in the turbine guide vane affecting its performance and service life

Method used

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  • Device for cooling guiding device group of turbine
  • Device for cooling guiding device group of turbine
  • Device for cooling guiding device group of turbine

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Embodiment Construction

[0021] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0022] see figure 1 and figure 2 , the present invention provides a device for cooling a turbine guider group, comprising a plurality of guide vane assemblies 1, a first outer edge plate mounting ring 21 with annular grooves respectively opened on the side ends, a second outer edge plate mounting ring 22 and An inner edge plate mounting ring 23 with an annular groove is opened on the periphery. Among them, a plurality of guide vane assemblies 1 are evenly distributed around the inner edge plate installation ring 23, and the two side ends of the guide vane assembly 1 are sleeved in the first outer edge plate installation ring 21 and the second outer edge plate installation ring respectively in the axial direction. 22 ring grooves.

[0023] combin...

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Abstract

The invention relates to a device for cooling a guiding device group of a turbine. The device comprises a plurality of guide blade components, a first external edge plate mounting ring, a second external edge plate mounting ring and an internal edge plate mounting ring; an annular groove is formed at the side end of the first external edge plate mounting ring; and an annular groove is formed at periphery of the internal edge plate mounting ring. The device provided by the invention provides three cooling channels to cool the guiding device group in an omnibearing mode, so that the greater heat stress caused by uneven temperatures of the guide blade components is reduced, and the heat stress situations of the blade bodies and the connection parts among the blade bodies, the internal edge plate and the external edge plate are improved particularly; and the crack caused by heat impact and heat fatigue phenomena is eased, and thus, the performance of the guiding device group is improved and the service life of the guiding device group is prolonged.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a device for cooling a turbine guide set. Background technique [0002] The working conditions of the turbine guide are very harsh, and it is the part with the largest heat load in the gas turbine. The temperature distribution of the guide vane is uneven, and it must bear large aerodynamic force and unstable pulsating load. Therefore, adopting effective cooling measures, lowering the operating temperature of the blades, and reducing the thermal stress of the blades are powerful guarantees for the safe and reliable operation of gas turbines. [0003] The prior art does not provide volumetric cooling of the deflector blades. It is common that the cooling air is introduced by the guide tube, impacts the inner cavity of the cooling blade through the orifice of the guide tube, and then is discharged through the slit of the trailing edge of the blade. The cooling air only cools the inner c...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/12
Inventor 杨家礼张亿力李久山黄舜刘秀芳季星星
Owner HUNAN HANGXIANG GAS TURBINE
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