LOW-PRESSURE TURBINE ROTOR Russian patent published in 2014 - IPC F01D5/08 F02C7/28 

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine rotors, particularly, to aircraft and surface gas turbine rotors. A turbine rotor comprises a labyrinth with an inner radial rib arranged at a gas downstream side of a disc rim and a flange fitted at the front side of the said disc. The said flange and disc rim make a circular air chamber connected at the outlet with a gas chamber and, at the inlet, via channels in a blade-to-disc joint, with the labyrinth inner chamber. The labyrinth is mounted at the disc as a radial flange connected to the radial rib by an elastic element. The labyrinth inner chamber is connected to a lock joint via the labyrinth radial flange groove exposed toward the disc. The air chamber on the disc front side is connected to the gas chamber via chamfers in a clock joint between the blade and disc. The ratio of the labyrinth circular rear rib axial length to the inner radial rib to the axial length of the labyrinth front circular front rib axial length relative to the inner radial rib makes 2…5. The ratio of the axial length of the labyrinth front circular rib radial length relative to the inner radial rib to the elastic element surface radius makes 1.5…3.

EFFECT: invention provides higher reliability and efficiency of the low-pressure rotor.

1 dwg