| 摘要 |
1,224,230. Jet propulsion plant - supporting centre-bodies. SOC. NATIONAL D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Sept.24, 1968 [Sept. 25, 1967], No.45386/68. Headings F1G and F1J. The invention relates to an arrangement for securing a centre body within an outer casing, for example for securing a centre body within an exhaust duct or an inlet duct of a jet engine. An intermediate support structure is mounted coaxially within the centre body and link members extend between the outer casing and the intermediate support structure. The link members comprise two groups of links inclined to the axis of the centre body, each link being pivotably connected at one end to the outer casing and at the other end to the intermediate support structure. The intermediate support structure comprises two parts adapted for relative axial movement and to which are secured the ends of the struts of the two groups of struts, the securing being arranged so that one set of pivot connections is displaced axially relative to the other set. In the jet nozzle assembly shown, a centre body 3 is supported within the duct 1, the centre body comprising parts 4, 5, 6, 7, 8, 9 within which is mounted an intermediate support structure 2 which comprises an inner cylindrical portion 12, 13 and an outer cylindrical portion 16, 17, 18, the two portions being inter-connected by flexible diaphragms 21, 22 which are formed with corrugations 21a, 22a whereby the two portions may move axially one relative to the other. The inner cylindrical portion 12, 13 is mounted on the spigot 10 of the centre body by means of a sleeve portion 11 of the portion 13. The outer cylindrical portion of the support structure is rigidly secured to the centre body by means of a frusto-conical member 23 and an assembly of pivotably-mounted links 24. Two sets of links 15, 20 are provided for supporting the centre body within the duct 1, the links 15 being pivotably connected to the duct 1 at 25 and to the inner cylindrical portion 13 of the intermediate support structure at 14, while the links 20 are pivotably connected to the duct 1 at the same points 25 and to the outer cylindrical portion 18 of the intermediate support structure at 19. In one embodiment each pair of links 15, 20 lies in a common plane but in a second embodiment links 15 and 20 alternate circumferentially. The struts 15 and 20 are enclosed within fairings 26. |
