DEVICE TO COOL GAS TURBINE ENGINE ROTOR DISC RECESSES, AND GAS TURBINE ENGINE Russian patent published in 2013 - IPC F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: proposed device comprises rotor disc with multiple axial recesses arranged along its edges, annular flange, annular retaining ledge, and multiple air feed holes. Said axial recesses are regularly distributed along disc rotational axis. Annular flange is directed toward inlet on disc inlet radial surface. Annular retaining ledge is located opposite disc inlet radial surface and comprises annular flange to make herewith an annular space. Said space makes the cooling air dissipation chamber. Said dissipation chamber outlet extends inside every disc recess at disc inlet end. Said multiple air feed holes are regularly distributed along disc rotational axis and extend into dissipation chamber at its inlet end. Said chamber incorporates means to decrease air flow rate arranged radially to extend air feed holes. Disc flange outer surface and/or retaining ledge flange inner surface has a bulge extending inside dissipation chamber. Said bulge serves to decrease flow section for air fed into said recesses. Every said bulge features maximum height at the level of disc recesses arranged in radial extension of appropriate air feed hole to make minimum air flow section. Minimum height between appropriate air feed hole and two adjacent holes are set to make maximum air feed flow section. Invention covers also gas turbine engine provided with above describes cooling device.

EFFECT: longer life.

5 cl, 4 dwg