TWO-STAGE TURBINE OF HAS TURBINE ENGINE Russian patent published in 2009 - IPC F01D9/02 F01D11/02 

FIELD: engines and pumps.

SUBSTANCE: two-stage turbine of has turbine engine comprises inner shelves of cooled second-stage nozzle vanes representing four-wall boxes with contact sites. Turbine interdisk space is sealed by front and rear intermediate disks that make together with aforesaid boxes a labyrinth seal. The said seal is divided into front seal arranged between front intermediate disk knife edges and mating surface of the box side wall with enlarged radial gap H, and rear seal. Contact sites are made on the front wall of the said box over its entire height. Front space of two-space nozzle vane communicates with slot-like space of front labyrinth seal with H/h=2…5, where H is radial gap of the front labyrinth seal, and h is that of the rear labyrinth seal.

EFFECT: higher reliability due to reduced temperature of vane contact sites and intermediate disk rim.

3 dwg