GAS TURBINE ENGINE COMPRESSOR ROTOR Russian patent published in 2010 - IPC F04D29/32 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine compressor rotor consists of impellers with cooling air intake system arranged inside the rotor. Proposed system consists of pipes (4) that takes air out from the circuit. Pipes (4) are arranged at upper ledge (5) with sections (6) of front impeller (8). Lower ledge (7) of impeller (8) has its sealing surface (9) coupled with mating ledge (10) of rear impeller (11). Grooves (3) to intake air from the circuit are arranged at the joint of impeller rims in front impeller (8) above oval pipes (4). Thrust shoulders (16) are arranged below ledge (7) on pipes (4). Pipes (4) have upper skew (17) and lower skew (19). Front impeller (8) has locking shoulder (14) with its amount L2 exceeding distance from shaft (12) to lower end of pipes (4) L1 by 3 to 5 mm. Sealing piston rings (13) are arranged below pipes (4) ahead of intake chamber.

EFFECT: higher reliability and longer life

4 cl, 5 dwg