INJECTOR OF GAS TURBINE COMBUSTION CHAMBER WITH DOUBLE FUEL SYSTEM AND COMBUSTION CHAMBER EQUIPPED WITH AT LEAST ONE SUCH INJECTOR Russian patent published in 2016 - IPC F23R3/28 F23R3/60 

FIELD: device for fuel combustion.

SUBSTANCE: injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit and an air circuit. Fuel injection circuit includes a starting fuel system and a main fuel circuit for operation in all flight modes after ignition. Fuel systems have parallel lines formed in common tube along longitudinal axis. Starting circuit is opened by one end, substantially in centre of spherical housing of injector, extending common tube. At end pipeline comprises injector ramp for driving fuel into rotation before its injection into chamber along central channel, passing through central wall of swirler. Channel of main circuit opens in annular channel formed in body opposite channels of jets arranged radially in main wall around central channel. Air circuit is directed between two parts of concentric spheres, formed by injector body and shell surrounding injector body and having a hole, which opens swirler.

EFFECT: invention widens range of operation without additional costs and higher mass.

11 cl, 5 dwg