GB703583A - Improvements in gas-turbine engines - Google Patents

Abstract

703,583. Gas turbine plant; axial-flow compressors. FIELDEN, G. B. R., WIGG, R. E., and RUSTON & HORNSBY, Ltd. Dec. 23, 1952 [Dec. 24, 1951], No. 30122/51. Classes 110 (1) and 110 (3) Rolates to a gas turbine engine; Fig. 1, comprising a turbine 12 driving an axial flow compressor 11 and including in addition to a main structure comprising an outer compressor casing, housings for compressor and compressor-coupled turbine bearings and an intermediate casing member supporting one compressor-bearing housing and the turbine-bearing housing, a separate compressor inlet duct 15, a separate compressor outlet duct 13 adapted to be coupled to an external combustion chamber 16 directly or via a heat exchanger 17, and a separate casing 14 enclosing a turbine inlet duct. To enable the external configuration of such an engine to be varied according to available accommodation, the compressor inlet duct, or the compressor outlet duct, or the separate casing, or all these parts, is or are coupled to the main structure by one or more circular flange joint with studs or bolts equally spaced circumferentially so that it oi they may be assembled in different angular positions about the rotational axis of the engine. A power turbine 21 with a two-branch exhaust 22 to the heat exchanger may be provided. The engine is supported from a bed-plate by brackets 24, 67, Figs. 5 and 5a, coupled to the inlet end of the compressor casing 23 and the intermediate casing member 58 respectively. The compressor inlet duct 15 surrounds a starter motor 38 and is secured to the compressor casing 23 and a bearing housing 28 by flange joints 32, 34 with evenly spaced bolt holes. The inner flange has evenly spaced holes 41 through any one of which an oil pipe 43 can pass to a lubrication duct in the bearing. A two-piece member 37 is secured to the bearing housing by studs 36 to form the inner wall of the compressor entry annulus. The outlet end of the compressor annulus forms an annular diffuser 30 the inner wall of which is formed by a separate two-piece member 31 secured by studs 45 to the bearing housing 29. The compressor casing 23 terminates in a flange 47 provided with equally spaced bolt-holes and is coupled to a complementary flange on the outer wall 51 of the separate outlet duct 13 by studs 49. An inner wall 52 of the duct is connected to the outer wall 51 by radial webs 53 forming guide vanes and is provided with' a flange 54 secured to a complementary flange on the bearing housing 29 by studs 56, the holes for which are equally spaced. The studs 56 also secure the bearing housing to one end of the intermediate casing 58. The journal 46 of the compressor: rotor is connected by a detachable flexible coupling 59 to an extension shaft 60 secured to the journal 61 of the turbine rotor. The journal 61 is supported in a bearing housing 65 secured by studs 66 to the intermediate 'casing. 58. A skirt 58a on the casing 58 terminates in a circular flange 68 with evenly spaced holes receiving studs 70 by which a complementary flange 71 of the turbine inlet duct casing 14 is secured thereto. The casing 14 encloses a duct attached by the inner margin of its annular outlet to a diaphragm member 73 secured by evenly spaced studs 74 to the intermediate casing 58. fhe stator of turbine 12 is unitary with the casing 14 and comprises an outer casing 75 secured thereto by studs 76 and a shroud ring 77 supported by elements 78 from the outer casing. The compressor outlet duct 13 terminates in a circular flange 80 with evenly spaced holes and the turbine inlet duct casing has a circular or oval inlet flange 82. The compressor casing, the members 37 and 31 and the bearing housings 28, 29 are split longitudinally on a horizontal plane so that the top halves can be removed to enable the compressor rotor to be lifted out.