ROTOR OF TWO-STAGE TURBINE Russian patent published in 2002 - IPC

FIELD: gas turbine engines of aircraft and ground applications. SUBSTANCE: rotor of two-stage turbine has working disks of first and second stages with working blades and heat shield in form of second intermediate disk with axial and radial channels in rim. Ratio of number of axial blades in rim of first intermediate disk to number of working blades of first stage is 1-4. Ratio of value of minimum distance between surface of channel and outer surface of rim of first intermediate disk to diameter of axial channel lies within 1.2 and 1.5. EFFECT: improved reliability of operation of turbine owing to improved efficiency of cooling of rotor intermediate disk rim. 3 dwg