TURBOJET ENGINE COMPRISING IMPROVED FACILITIES OF REGULATION OF FLOW RATE OF COOLING AIR FLOW TAKEN AT OUTLET OF HIGH PRESSURE COMPRESSOR Russian patent published in 2014 - IPC F01D5/08 F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: turbojet engine comprises an inlet channel of a cooling air flow of a disc of a high pressure turbine opening into a cavity. The cavity is substantially isolated at the inlet side from the cavity, in which air flow circulates, being taken from the outlet of the high pressure compressor, the first labyrinth seal and at the outlet side of the cavity communicating with the primary channel of the turbojet engine, the second labyrinth seal. The turbojet engine comprises channels communicating with the inlet channel and opening via a fixed part of the first labyrinth seal between two ribs of this seal for provision of passage of air flow arriving from the inlet channel between these ribs.

EFFECT: invention is aimed at increased cost-effectiveness of cooling, reduced rated value of air flow rate of cooling of an inlet wheel of a high pressure compressor in a turbojet engine.

6 cl, 4 dwg