| 摘要 |
1,204,698. Gas turbine ducted fan engines; combustion equipment. UNITED AIRCRAFT CORP. Nov.29, 1967 [Dec.5, 1966], No.54323/67. Headings F1J and F1L. A gas turbine jet engine of the by-pass or ducted fan type is provided with re-heat combustion equipment in the region where the turbine exhaust gases and the by-pass air-flow mix and downstream of the re-heat equipment the gases flow through a curved exhaust duct, means being provided to ensure that the combustion gases from the re-heat section are surrounded by a layer of unburned air as the gases flow through the curved exhaust duct. In Fig. 1 the turbine exhaust gases discharge through duct 18 and the by-pass air-flow discharges through annular duct 20, the two streams discharging into a common duct 10, the two flows being suitably matched. Re-heat combustion equipment comprising a fuel nozzle assembly 28, 30 and flame stabilizing equipment 4 are disposed in the duct 10 and downstream of the re-heat equipment the gas duct 15 is in the form of a bend whereby the exhaust gases discharge at an angle to the flow through the engine. The total pressure of the exhaust gases and by-pass air is substantially uniform across the duct upstream of the re-heat equipment. Combustion is caused to occur within a controlled profile indicated at 29, so that the central core of combustion gases is surrounded by a peripheral stream of unburned air, the peripheral stream of air having a greater total pressure than the central core of hot gases. This lowers the rate at which the cooling boundary layer is dissipated as the core of hot gases and the peripheral layer of air pass through the curved exhaust duct. The theory of the invention is set forth in the Specification. |
