COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2009 - IPC F04D29/08 

FIELD: engines and pumps.

SUBSTANCE: invention is related to compressors of gas-turbine engines and increases reliability and tightness of disc-labyrinth joint. Beyond-compressor labyrinth is installed in compressor of gas-turbine engine on disc of the last stage with the help of peripheral joint. Channels are arranged in labyrinth web. Closed cavity between disc and labyrinth is connected via channels to unloading beyond-compressor cavity of low pressure. Cavity is connected to compressor flow path via radial and axial clearances in peripheral joint. Sealing combs of labyrinth are arranged with external diametre decreasing from disc. Ratio of passage area of channels in F1 labyrinth web to passage area of axial clearances in peripheral joint of disc with F2 labyrinth is within the limits of 10…30. Ratio of external diametre of sealing comb D nearest to disc to external diametre of sealing comb d that is most distant from disc is within the limits of 1.02…1.2. By pressing beyond-compressor labyrinth to the last stage compressor disc by means of gas forces reliability and tightness of disc-labyrinth joint are increased at all modes of gas-turbine engine compressor operation.

EFFECT: increased reliability and tightness of disc-labyrinth joint in all modes of gas-turbine engine compressor operation.

2 dwg