| 摘要 |
675,300. Gas turbine and jet propulsion plant. ROLLS-ROYCE, Ltd. May 23, 1950 [May 24, 148; May 24, 1949], Nos. 13906/49 and 13907/49. Class 110(iii) A gas turbine engine has an exhaust assembly 15 which comprises in combination an outer tubular structure 19 which is partly supported from the engine and forms the main loadbearing structure of the assembly, an imperforate, tubular, exhaust member 20 which is supported within the structure for axial relative movement therebetween and defines an annular air passage therewith, air inlet means to the passage formed in the end of the structure adjacent the engine, air outlet means from the passage adjacent its end remote from the engine and gas sealing means to prevent leakage of exhaust gases into the passage. The structure 19 comprises a tubular member 24 having reinforcing webs 25 welded thereon and a frusto-conical part 21 which are interconnected by a bolted flanged connection. The part 21 has a cylindrical extension which is bolted to the engine and the structure 19 is secured by pivoted links 18 to the aircraft. The exhaust nozzle 16 comprises a pair of interlinked segments 16a, each having inner and outer walls 32, 33 respectively and being operated by a hydraulic ram 31 pivoted to the member 24. The rams are enclosed in a two-part housing 27, 28 which is connected by a welded plate 30 to the member 24 and carries a spring metal seal 35 for co-operation with the segments 16a. The exhaust member 20 comprises intersliding sections 20a, 20b. The section 20a is secured to the structure 19 by at least three straps 43 which are welded to the section 20a and extends tangentially therefrom. The straps are riveted to a ring which fits within the structure 19 and is secured thereto by bolts 45 passing through an outer reinforcing ring 46, the wall 19 and the inner ring to engage nuts 45a welded thereon. The section 20b is secured by tangential and axially arranged straps 43, 47, respectively; the inner ring being dispensed with and the nuts welded to the straps 43. Cooling air enters the passage through ports in the part 21 and is discharged between a ring 48 on the section 20b and the wall 33. The ring 48 is adapted to engage a ring 36 on the segments 16a to limit their movement and provide a gas seal therewith whereupon the cooling air flows through the spaces between the walls 32, 33 and escapes through ports 34. Specification 640,428 is referred to. |
