GAS-TURBINE ENGINE AFTERBURNER Russian patent published in 2003 - IPC

FIELD: aircraft industry. SUBSTANCE: proposed afterburner of gas-turbine engine contains behind-turbine channel and prechamber including V-shaped flame stabilizer accommodating burners which are connected with hollow intakes through holes in stabilizer top, intakes being coupled with nozzles and with fuel supply pipelines. Fuel-gas and gas radial swirlers with blades featuring opposite twist are arranged in walls of burner housing in series with gas-air duct. Each burner housing is connected from flow inlet side with cylindrical thrust and floating bushings. Inner space of floating bushing is in contact with outer surfaces of fuel nozzle, and at other side, outlet of burner housing swirler nozzles is connected with inner space of V-shaped stabilizer. Outlet of gas swirler nozzles is connected through conical wall with hollow cylindrical inner shell. Cylindrical flange with uniformly spaced through holes over circumference is located on outer surface of burner housing, through holes being connected with space formed by cylindrical hollow inner shell and outer shell with longitudinal ribs on inner surfaces connected to rear end face of flange. Longitudinal ribs are in contact with outer surface of cylindrical inner shell. Front end of burner housing flange is connected with hollow intake curved in direction of gas flow whose inlet cross section is square to gas flow of through duct and is located from minimum cross section of behind-turbine channel at a distance defined by claimed ratio. EFFECT: provision of optimum combination of hydraulic losses high combustion efficiency and reliable operation of afterburner. 3 dwg