ROTOR OF HIGH-TEMPERATURE TURBOMACHINE Russian patent published in 2014 - IPC F01D5/06 F01D11/02 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rotors of high-temperature turbomachines of gas turbine engines of aviation and ground use. In a rotor (1) of a high-temperature turbomachine between the first (7) and second (8) and the last but one (9) and the last (10) along gas flow (11) sealing combs in a rim (6) of an intermediate disc 5 there are radial channels (13) and (14), connecting an air disc-to-disc cavity (4) with a gas cavity (12) of the turbine. Radial walls (15) and (16) of channels (13) and (14) are made flat, and walls (17) and (18) that connect them are made cylindrical. The ratio of the length L of the channel in circumferential direction to the radius R of the cylindrical wall of the channel is within 2…6.

EFFECT: by exclusion of contamination of inner surface of an intermediate disc and reduced concentration of stresses in a disc rim, high-temperature turbomachine rotor reliability increases.

2 dwg