SEAL ASSEMBLY FOR GAS TURBINE ENGINE INCLUDING GROOVES IN INNER BAND Russian patent published in 2017 - IPC F01D11/00 F01D11/04 F01D5/08 

FIELD: engine devices and pumps.

SUBSTANCE: seal assembly between a disc cavity and a hot gas channel passing through the turbine section of a gas turbine engine comprises a rotating blade assembly and a stationary assembly of guide blades. The rotating blade assembly includes a plurality of rotor blades which rotate together with the turbine rotor during operation of the engine. The fixed assembly of the guide blades includes a plurality of guide blades and an inner casing. The inner casing includes a radially outward facing first surface, a radially inward facing second surface, and a plurality of grooves extending from the second surface. The grooves are arranged so that a region having an extent in the circumferential direction is formed between adjacent grooves, at that during operation of the engine the grooves direct the purge air from the cavity of the disc towards the hot gas channel so that the purge air flows in the required direction with respect to the direction of the hot air flow through the hot gas channel. The grooves taper away from their inlets spaced from the axial end portion of the inner band to their outlets positioned near the axial end portion of the inner band so that the inputs have a width larger than the outputs.

EFFECT: invention makes it possible to prevent the ingress of hot gas into the turbine disc cavity the turbine engine more effectively.

9 cl, 4 dwg