A turbine disk with a cavity sealing structure

Abstract

The invention discloses a turbine disk with a cavity sealing structure, which comprises a turbine static disk and a turbine moving disk; the inner and outer sealing rings of the static disk extend outwardly on the side of the static disk between the edges of the rotating and static turbine disks, and the outer and outer sealing rings of the turbine moving disk side There is an inner sealing ring of the moving disk; the first end of the inner sealing ring of the static disk or near the wall of the static disk is provided with a ring-shaped boss ring protruding toward the high radius direction, and the end of the inner sealing ring of the static disk is at or near the wall of the static disk. The end position is provided with an annular protruding ring that protrudes toward the high radius direction; the outer cavity of the static disk formed by the sealing structure, on the one hand, allows the gas to be generated between the outer sealing ring of the static disk and the inner sealing ring of the moving disk. The vortex effectively prevents the intrusion of part of the high-temperature gas at the outlet of the sealed cold air, and consumes part of the intruding high-temperature gas; The gas in the deep cavity is used to prevent the gas from invading the sealed inner cavity; under the premise of a certain amount of gas used for sealing, the gas can be better blocked in the outer cavity of the static plate, so the sealing performance has been greatly improved.

Description

technical field [0001] The invention belongs to the technical field of engines, in particular to the technical fields involving rotating parts such as gas turbines and aeroengines. Background technique [0002] The study of gas turbine aerodynamic heat transfer is of great significance in the fields of science and technology. [0003] The continuous improvement of gas turbine inlet parameters and the decline of cooling air quality lead to an increase in the thermal load on high-temperature hot-end components. Therefore, an advanced secondary air cooling system needs to be designed to prevent overheating of rotating components such as discs, blades and rotors, and reduce its thermal stress level. As one of the important components of the gas turbine advanced secondary air cooling system, the flange seal has also become one of the key technologies in the development of gas turbines. [0004] Gas intrusion is a serious problem that can be encountered in the rotor-stationary d...

AI Technical Summary

Problems solved by technology

The high-temperature gas goes deep into the center of the disc along the rotating-static disc cavity, resulting in uncontrollable deformation and fatigue of the disc, serious damage to nearby bearings, etc.

The main way to reduce gas intrusion is to increase the gas supply to the panel cavity. The cooling gas introduced from the compressor can effectively prevent the intrusion of mainstream gas, but excessive extraction of cold air from the compressor will inevitably lead to a decrease in the overall thermal efficiency of the engine; another measure It is to set the rim seal on the outer diameter of the turbine disk to increase the flow resistance of the intruding gas

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