| 摘要 |
1533551 Gas turbine ducted fan engines GENERAL ELECTRIC CO 21 Oct 1975 [8 Nov 1974] 43163/75 Heading F1J A gas turbine engine comprises a nacelle radially spaced from and circumscribing the engine, support means extending between the engine and the nacelle so as to support the nacelle in position with respect to the engine. The invention is described with reference to a gas turbine ducted fan engine which comprises a core engine 12, a fan casing or nacelle 28, a fan assembly 14 mounted within the casing, air delivered by the fan passing in part through inlet 32 into the core engine and in part through the fan duct 26 finally discharging from the fan nozzle 30. The engine is mounted below an aircraft wing 46 by a pylon 44 which comprises a support structure 48. The pylon defines a space 51 within which engine and aircraft accessories 50 mounted on the engine are located. The pylon is mounted on the core engine by means of a wheel-shaped structure which comprises a pair of inner ring members 88, 90 which are secured to engine structure 92, and intermediate ring members 96, 98 which are located within the hollow wall structure which defines the outer wall of the core engine 12 and the inner wall of the fan duct 26. The ring members 88, 96 and 90, 98 are inter-connected by radial spoke or strut members 102, 104 formed integrally therewith, the spoke members being enclosed within fairings 110 which provide a faired surface for air-flow through the core engine inlet passage 32. The wheel-shaped structure comprises also a pair of outer ring members 72, 74 which are inter-connected with the intermediate ring members 96, 98 by means of radial spoke or strut members 106, 108 formed integrally therewith. The spoke members 106, 108 are enclosed with fairings 112 which provide a faired surface for air-flow through the fan duct 26. The outer ring members 72, 74 are secured to the fan casing or nacelle 28 by means of flanged members 76, 78, 80 and angle members 82, 84, 86. The fan casing comprises inner, outer and intermediate walls 60, 62, 64 with honeycomb material 58 disposed therebetween. The fan casing downstream of the support structure may comprise a pair of doors 124, 126 hingedly connected at 128, 130 Fig. 5 to a rearwardly-extending fixed element 122. The core engine 12 and support structure is supported from the pylon structure 48 by means of a mounting assembly 54 comprising a thrust rod 148 and a mount 146 formed integrally with the intermediate ring member 98; the support comprises also a rear mounting 144. An inlet duct portion 137 is secured at the upstream end of the support structure. An abradable element 66 is secured within the fan casing 28 around the periphery of the fan blades 15, the element being formed with corrugations 68. |
