Turbine disc with T-shaped disc edge sealing structure

Abstract

The invention discloses a turbine disc with a T-shaped disc edge sealing structure. The turbine disc comprises a turbine movable disc, a turbine static disc and a cold air channel between the turbine movable disc and the turbine static disc, wherein a first-stage sealing ring is arranged on the outer disc edge of the turbine static disc, a second-stage sealing ring is arranged on the inner wall face of the turbine movable disc, a third-stage sealing ring is arranged on the inner wall face of the turbine static disc, T-shaped protruding rings with T-shaped cross sections are arranged at the ends of the second-stage sealing ring and the third-stage sealing ring correspondingly, the T-shaped protruding rings comprise wide parts and narrow parts, and the tail ends of the narrow parts of the two T-shaped protruding rings are connected with the extending tail ends of the second-stage sealing ring and the third-stage sealing ring correspondingly. Due to the fact that the T-shaped protruding rings extending towards the two ends are arranged at the extending tail ends of the sealing rings, a flow area is reduced, the flow resistance is increased, high-temperature fuel gas forms vortexes in a cavity between the second-stage sealing ring and the first-stage sealing ring, fuel gas invasion is resisted, the sealing efficiency is greatly improved while clearance distances between the sealing rings and the movable and static discs are maintained in a reasonable range, and due to a zigzag cold air channel, the sealing performance is improved.

Description

technical field [0001] The invention relates to an aero-engine turbine disk, in particular to a turbine disk with a T-shaped flange seal. Background technique [0002] The disc rotor is widely used in the design of turbine components because it adapts to the special working conditions and rotational and static characteristics inside the turbine. [0003] Due to the inherent rotational and static characteristics of the turbine, the high-temperature gas in the main channel will enter the disk cavity through the gap between the dynamic and static disks, causing the turbine disk to be ablated. In order to protect the aero-engine turbine disc and prevent the core components from being damaged by high-temperature gas penetrating into the disc cavity, a disc edge sealing structure is usually set up and the cold air from the compressor is introduced into the rotor-stationary disc cavity to resist the intrusion of high-temperature gas. [0004] The currently used disk edge sealing s...

AI Technical Summary

Problems solved by technology

However, the sealing effect of the turbine disk with this disk edge sealing structure is limited, and the sealing effect is usually improved by reducing the sealing ring gap, but in the case of high-speed rotation of the turbine turntable, the gap is too small to cause the sealing ring to collide and damage

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