Abstract: A flow inducing means 110 for use in an anti-icing system for a nose bullet 10 of a gas turbine engine of the type in which hot gas is caused to flow along the center of a rotating tube 7,62 towards the nose bullet 10 to heat it, and cooled air is centrifuged to the surface of the bore of the tube 7,62 and is displaced rearwardly along the tube. The tube 7,62 is open at its rear end, and the flow inducing means 110 is positioned adjacent the open end. The flow inducing means 110 comprises a plurality of radial vanes 111 which enters in a radially inwards direction and the vanes 111 are shaped and positioned to redirect the gas axially along the center of the tube 7. The flow inducer 110 may include a shroud 115 which has a circumferential inlet opening and an axial facing outlet 116. The shroud may serve as a flow separator which separates the incoming hot gas from the cooled gas exiting the tube.

Abstract: A combustor for a gas turbine engine. The combustor employs an array of fuel injectors arranged across and in the mouth plane of the combustor flame tube. Each injector has a baffle plate through which the injector nozzle projects, the baffle plate having axial holes for atomization air to intercept and atomize radial fuel jets from the injector nozzle. Cooling of the flame tube is performed by full coverage impingement and effusion without disturbing the cooling film by entry and penetration of transverse air jets. Flame stabilization is achieved under all required operating conditions by the radial-fuel/axial-air atomization in conjunction with the baffle plates. Comprehensive combustion mixing and dilution is achieved by the uniformly distributed supply of up to 90% of the total air supplied to the combustor around and through the baffle plates.