DE2060401

1284439 Spray burners ROLLS ROYCE Ltd 9 Dec 1969 59965/69 Heading F4T A fuel injector for a gas turbine engine comprises two concentric nozzles 30, 32 supplied with liquid fuel from ducts 42, 44 a shroud member 54 which forms an annular nozzle 38 supplied with gaseous fuel from a duct 46, and a cowl member 56 which defines an annular flow passage 62 and supports a conical baffle 60, the fuel from the central nozzle 30 impinging on a deflector 36 to reduce the spray angle, and the annular flow passage 62 being fed with combustion air. The central nozzle 30 is formed by drillings 48 in a nozzle member 28 clamped to a member 24 by a nut 26 which forms the nozzle 32 and the deflector 36. A heat-resistant plate 72 is secured to the baffle 60 so that, in use, heat is transferred to the baffle to prevent carbonizing thereof. The liquid fuel ducts 42, 44 are connected to an annular manifold (82, Fig. 1) connected to a fuel control unit (88) by a line 86. The gaseous fuel duct 46 is connected to an annular manifold (74) connected to the fuel control unit by a line (84) having a valve (92) and connected to a turbine compressor (12) by a line (94) containing a valve (90). When the gaseous fuel valve (92) is closed the valve (90) is opened so that high pressure air is supplied to the nozzle 38 to prevent "burn-back".