| 摘要 |
622,384. Gas turbine plant for jet-propulsion. RUBBRA, A. A. March 14, 1947, No. 7219. [Class 110(iii)] In a gas turbine plant for jetpropulsion of aircraft, the exhaust assembly 13, the stator part 22 of the turbine, the inner and outer rings 20, 24 which support the guide vanes 25, the ends 12 of the combustion chambers and the nozzle boxes 30 are carried by a ring piece 29 which is secured to an intermediate casing 19, as described in Specification 610,113. The ring piece is of such a form that all its surface can be machined by turning. Both surfaces of the conical and cylindrical end parts 29b, 29c and the up-stream side of the intermediate part 29a, which is apertured to receive the combustion chamber ends, are produced by simple turning about the turbine shaft axis. The downstream side of the intermediate part 29a is spherical about the apex of the cone on which the axes of the combustion chambers lie. The apertures in the ring piece 29 are fitted with rings 42, which have flanges 44 and the contacting sides of these flanges are spherical. The intermediate part 29a thickens towards its middle and between the apertures, as shown in Fig. 5, and the middle portions are lightened by grooves 40. The ends of the nozzle boxes 30 have springy flanges 35 which engage the rings 42, the ring 31 and the end of the part 28. |
