GB600946A - Improvements in or relating to gas-turbine power-plants - Google Patents

Abstract

600,946. Gas turbines; jet propulsion. BRISTOL AEROPLANE CO., Ltd., and OWNER, F. M. June 21, 1945, No. 15880. [Class 110 (iii)] A gas turbine plant for aircraft is constructed to take interchangeable turbines and interchangeable housings 18. As shown in Fig. 1, the housing 18, which is secured to the compressor casing 17, includes the drives for auxiliaries 19, 20, 22 and a reduction gear through which an air-screw shaft 23 is driven. When the plant is used solely for jet propulsion, an alternative housing 24, Fig. 3, is fitted. Pinions 30, 34 project from the compressor casing into the housing and engage wheels 31, 33 from which the auxiliaries are driven. Auxiliaries 26, 27 may be separately detachable in one piece and when they are not in place the end of shaft 32 is enclosed in a cap. The turbine casing 35a, 35b is removably secured to the compressor casing and the end 34 of the turbine shaft is splined at 46 to the compressor shaft 28 so that the turbine can be removed as a whole. A cylindrical extension 36 on the turbine casing is slidingly mounted in a sleeve 38 on the compressor casing and the part 35b is supported by radial pins 41 carried in a ring 39 supported at the apices of triangular bracings 40 anchored to the compressor casing. The turbine casing may be made in two parts 35a, 35b which are slidingly connected at 35c and are relatively located by the radial bushes 42, which pass through holes in the ends of arms 43 of the part 35a and enter sockets in the part 35b. These bushes provide sockets to receive the pins 41. The plant shown in Fig. 1 has a compressor taking in air at 16 to an axial stage 13 which is followed by a centrifugal stage.