Turbine disk cavity sealing structure with bypass gas entraining

Abstract

The invention belongs to the field of gas turbine engines, and relates to a turbine disk cavity sealing structure with bypass gas entraining. The turbine disk cavity sealing structure with bypass gasentraining comprises an inner support ring assembly provided with an inner support ring gas inlet hole, a front baffle plate assembly, a pre-rotation nozzle, a first gas passage for transferring a first path of cold gas output by the pre-rotation nozzle, a second gas passage for transferring a second path of cold gas output by the pre-rotation nozzle, and a third gas passage arranged between the inner support ring assembly and the front baffle plate assembly, wherein the third gas passage comprises a first sealing device arranged between the inner support ring assembly and the front baffle plate assembly, a sub gas passage and a bypass gas entraining passage; a third path of cold gas output by the pre-rotation nozzle flows into the sub gas passage and the bypass gas entraining passage through the first sealing device; and gas output by the third gas passage flows toward a high-pressure turbine movable blade.

Description

technical field [0001] The invention belongs to the field of gas turbine engines, and relates to a sealing structure of a turbine disk cavity with bypass bleed air. Background technique [0002] The working principle of a gas turbine engine is to use the high-temperature and high-pressure gas generated by the mixed combustion of compressed air and fuel from the compressor to drive the turbine to rotate at high speed, and the turbine drives the compressor through the turbine shaft to form a continuous operation. A turbine consists of stationary vanes (which make up the stator part) and rotating blades (which make up the rotor part). In order to ensure the reliable operation of the turbine rotor and avoid friction between the rotor and stator, there is a certain gap between the rotor and stator turbine discs. The existence of axial and radial gaps between the guide vane and the root of the moving blade may cause high-temperature gas in the turbine channel to invade the turbin...

AI Technical Summary

Problems solved by technology

Although the introduction of sealed cold air can prevent the mainstream gas from invading the ablation disk cavity, but due to the low flow rate of sealed cold air entering the main channel and the small air pre-swirl angle (compared with the pre-swirl angle of the outlet at the root of the guide vane), the sealed cold air will Intense mixing with mainstream gas at the outlet of the sealing seam, resulting in increased losses and reduced turbine efficiency

With the increase of turbine speed, temperature before the turbine and efficiency requirements, the low flow rate and low pre-swirl angle of the sealed cold air between the rotor and the stator cause the performance degradation of the turbine to become more and more obvious

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