GAS TURBINE ENGINE Russian patent published in 2011 - IPC F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine includes HP compressor, combustion chamber and HP and LP turbines with cooled nozzle diaphragm of LP turbine and cooling channel of inter-disk cavity with supply manifold at the inlet. Cooling channel of inter-disk cavity is separated from flow part of turbine by means of labyrinth seal and slot-type gap. Supply manifold of cooling channel of inter-disk cavity through inlet manifold of cooling system of LP turbine nozzle blades and heat exchanger installed in the second engine loop is connected to axial unloading cavity of compressor. Supply manifold of cooling channel of inter-disk cavity is separated from inner cavities of cooled nozzles blades, and its connection to inlet manifold of cooling system of nozzle blades is provided by means of transit tubes installed in inner cavities of nozzle blades with a gap relative to their walls. Transit tubes are equipped with calibrated sections.

EFFECT: invention allows decreasing the temperature of cooling air supplied to inter-disk cavity to cool the side surfaces of turbine disks.

4 cl, 4 dwg