FIELD: devices for fuel combustion.
SUBSTANCE: method of fuel injection is implemented by means of an air-fuel mixing system with geometrical axis of central symmetry (X′X), into the gas turbine engine combustion chamber. Fuel injection is performed in the mixing system along axis (C′C) parallel to symmetry axis (X′X) of this system and different from that axis (X′X). Combustion chamber arranged in the housing has an angular displacement relative to the housing. Fuel injection is performed by means of a nozzle rigidly attached to the housing, and the mixing system rigidly attached to the combustion chamber.
EFFECT: invention is aimed at decrease and even elimination of instability phenomena of combustion process in gas turbine engine due to fuel injection along the axis decentered relative to air-fuel mixing system, leading to the fuel flow, which is not perfectly axially symmetric any more.
7 cl, 4 dwg
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