Gasturbine, insbesondere Kleingasturbine

摘要

962,057. Gas turbine plant; gas turbine blades. B M W TRIEBWERKBAU G.m.b.H. April 24, 1962 [April 25, 1961], No. 15571/62. Headings F1G and FIT. A gas turbine engine comprising a radial or diagonal outward flow combustion chamber located between a radial or diagonal flow turbine and a radial flow compressor has supporting plates, between the chamber and the turbine and between the chamber and the compressor, locating seals and the chamber walls, such that the supporting plate between the chamber and the turbine is rigidly fixed to a cold part of the turbine casing by elements extending through the hollow nozzle vanes of the turbine, whereas the turbine nozzle ring is fixed to this assembly or to other structural parts of the gas turbine in a manner permitting relative movement by thermal expansion. A supporting plate 4, Fig. 1, carrying a labyrinth seal is located between the turbine 1 and the wall 3 of a combustion chamber 2. A similar supporting plate (not shown) is located on the compressor side of the combustion chamber 2. The plate 4 is rigidly secured to the turbine casing 10 by a screw 9 in a bush 6 passing through the hollow turbine nozzle vane 5 and flanges 7 and 8. Screw 9 also secures the combustion chamber wall 3. The nozzle vane ring 11 is connected, for example welded, to the flanges 7 and 8 with the interposition of expansion joints 12 and 13 such that cold compressor air 15 passes through the vanes 5. In a modification, Fig. 2, the supporting plate 41 is fixed to the turbine casing 101 by bolts 16 passing through bushes 61 and nuts 17, 18. Nozzle ring 111 is non rigidly attached to the plate 41 by an expansion collar 19. Bush 61 is slightly wider than the ring 111. In a further modification, Fig. 3, the nozzle ring 1111 is connected to the combustion chamber walls 311 and 25 by sliding joints 23 and 24 and rigidly attached to the supporting plate 411 or to some other stationary part of the casing by members 27 and 28 with the interposition of seals 29 and 30. Threaded bushes 20 are secured to the plate 411 and connected at stepped joint 26 with threaded bushes 21 on the casing 1011 by screws 22 passing through the nozzle vanes 511 such that the fixing elements are cooled by compressor air 1511. In a further modification, Fig. 4 (not shown), a spring member holds the nozzle ring in contact with a centring face to prevent flapping of the ring.