Gas turbine rim sealing structure and method

A gas turbine and sealing structure technology, applied in mechanical equipment, engine components, machines/engines, etc., can solve problems such as the adverse effect of mainstream aerodynamic efficiency and the limited reduction of sealed air-conditioning volume.

Active Publication Date: 2016-09-28
SHANGHAI ELECTRIC GAS TURBINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, in practical engineering applications, the radial rim seal is usually used instead of the traditional axial rim method, which can reduce the amount of sealed cold air without gas intrusion, but only by setting the

Method used

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  • Gas turbine rim sealing structure and method
  • Gas turbine rim sealing structure and method

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Embodiment Construction

[0030] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. These embodiments are only used to illustrate the present invention, but not to limit the present invention.

[0031] In the description of the present invention, it should be noted that the terms "center", "portrait", "horizontal", "top", "bottom", "front", "rear", "left", "right", " The orientations or positional relationships indicated by vertical, horizontal, top, bottom, inside, and outside are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying It is described, rather than indicated or implied, that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention. Furthermore, the term...

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Abstract

The invention relates to the technical field of gas turbines, in particular to a gas turbine rim sealing structure. The structure comprises a static vane connected to a static vane platform and a movable vane connected to a movable vane platform, wherein an airtight cool air channel is formed between the static vane platform and the movable vane platform, blowing holes are formed in the peripheral direction of the static vane platform and communicated with a static vane cooling channel, an outlet of each blow hole is located on the downstream side of the static vane platform and communicated with the airtight cool air channel, and the blow holes are used for guiding cooling air in the cooling channel out and making cooling air form an air curtain at the position of an outlet of the airtight cool air channel. The invention further relates to a rim sealing method. By the adoption of the method, cooling air in the static vane cooling channel can be guided out from the downstream side of the static vane platform, and the air curtain can be formed by cooling air at the position of the outlet of the airtight cool air channel. The air curtain can improve the airtight performance of the gas turbine rim sealing structure, reduce airtight cool air amount, reduce the influence of airtight cool air on aerodynamic efficiency of main current, and improve overall efficiency.

Description

technical field [0001] The invention relates to the technical field of gas turbines, and in particular, to a gas turbine rim sealing structure and method. Background technique [0002] Heavy-duty gas turbines mainly include three major components: compressor, combustion chamber and turbine. After the air enters the compressor, it is compressed into high temperature and high pressure air, which is supplied to the combustion chamber for fuel combustion. The generated high temperature and high pressure gas expands in the turbine to do work, and then is discharged into the atmosphere or waste heat boiler and other equipment through the exhaust diffuser. [0003] After the high-temperature gas in the main flow channel of the turbine flows through the stator vanes, a high-pressure flow area and a low-pressure flow area are alternately formed in the middle area of ​​the rotating and static components along the circumferential direction. In the high-pressure flow area, the pressure...

Claims

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Application Information

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IPC IPC(8): F01D11/10
CPCF01D11/10
Inventor 计京津孙博黄丹萍
Owner SHANGHAI ELECTRIC GAS TURBINE CO LTD
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