Gas turbine rim sealing structure and method

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, in particular to a gas turbine rim sealing structure and method. Background technique [0002] A heavy-duty gas turbine mainly includes three major components: a compressor, a combustor, and a 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 high-temperature and high-pressure gas generated 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 channel of the turbine flows through the vanes, high-pressure flow areas and low-pressure flow areas will be formed alternately along the circumference in the middle area of ​​the rotor-stationary components. In the high-pressure flow area, the pressure of the main flow channel is h...

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 radial rim seal to seal The reduction of the cold air volume is limited; and the cold air directly enters the main flow channel at a 90° direction, which will also have an adverse effect on the aerodynamic efficiency of the main flow

Images