FUEL-AIR BURNER OF COMBUSTION CHAMBER OF GAS-TURBINE ENGINE

FIELD: gas-turbine engines. SUBSTANCE: fuel-air burner of combustion chamber of gas-turbine engine includes fuel injector in the form of body with holes to supply and atomize fuel, axial and tangential air swirl vanes in the form of conduits with open butts and blades inside, air flow stabilizer. The latter is placed between rear wall of nozzle body and inlet butt of axial air swirl vane to form slit conduit with its inlet butt. Each swirl vane is provided with contraction-diffuser nozzle. Ratio of flow area of contraction-diffuser nozzle of axial and correspondingly tangential swirl vanes to flow area of burner amounts to (0.90-1.05). Flow area of slit conduit formed by air flow stabilizer amounts to (0.50-0.85)N of flow area of burner, where N= . Angle confined between axis of burner and outlet edges of nozzles of axial and tangential swirl vanes is equal to angle of arrangement of outlet edges of blades of axial swirl vane across its medium diameter relative to its outlet butt with deviation of 5 degrees. EFFECT: improved fuel efficiency of gas- turbine engine, widened range of its stable operations, provision for reliable re-start of engine under high-altitude conditions. 1 cl, 3 dwg