Gas turbine jet propulsion engine

摘要

1,127,660. Gas turbine ducted fan engines. ROLLS ROYCE Ltd. Sept. 5, 1967 [Sept. 17, 1966], No.41603/66. Headings F1J and F1T. A gas turbine ducted fan engine comprises a gas turbine type gas generator, a further turbine adapted to be driven by gases from the gas generator and a fan coaxial with the gas generator and adapted to be driven by the further turbine, the further turbine comprising at least one radial flow rotor stage. The engine shown in Fig. 1 is particularly suitable for use as a vertical lift engine and comprises a gas generator 10, a turbine section 11 and a fan section 12. The gas generator section comprises LP compressor 15, HP compressor 16, combustion section 17, HP turbine 18 and LP turbine 19, the HP turbine being connected to drive the HP compressor through shaft 21 and the LP turbine being connected to drive the LP compressor through shaft 20. Gases from the gas generator pass to the turbine section 11 which comprises a right angle bend portion 23 having stator blades 22, a first radial flow rotor stage 24, a radial flow stator blade assembly 26, a second radial flow rotor stage 28, an axial flow stator blade assembly 30 and an axial flow rotor stage 31. The turbine rotor stage 24, 28 and 31 are connected to a rotor assembly 25, 32 and also by means of the shroud member 29 and extension 40, to the fan blade assembly 41, the whole rotary assembly being supported on bearings 42, 35. The fan blades rotate within a duct defined by an outer shroud 43, which is supported by struts 44 disposed upstream of the fan blades and by struts 45 downstream of the fan blades. The bearing 42 is supported on the casing 14 of the gas generator, and the bearing 35 is supported on a tubular member 36 which is supported by struts 37 which extend through the stator blades 22; the member 36 is also supported by struts 38. In Fig. 2 the gases from the gas generator are turned through 180 degrees in a bend 50, the gases then being turned through 90 degrees to flow radially outwardly, the gases being directed by stator blades 51 on to a radial flow rotor stage 52, a radial stator stage 53. a radial flow rotor stage 54 in which the gases are turned through 90 degrees to flow in a downstream direction through an axial flow stator 55 and an axial flow rotor stage 56. The rotor stages 52, 54 and 56 are inter-connected and drive fan blades 58. The rotor assembly is supported at its downstream end in a bearing 60. The fan blades rotate in a duct defined by an outer shroud 65 which is supported by struts 66 located downstream of the fan blades. This engine is of reduced axial length compared with that of the first embodiment. In a further embodiment the engine is similar to that of Fig. 2 but the stator stages of Fig. 2 are now rotor stages and the rotor stages are now stator stages.