GB742612A - Mounting rotor shafts of compound gas turbine engines - Google Patents

Abstract

742,612. Gas-turbine plant. ARMSTRONG SIDDELEY MOTORS, Ltd. June 14, 1954 [July 3, 1953], No. 18448/53. Class 110(3) In a gas-turbine engine having at least two separate compression sections and at least two separate turbine sections, the lower-pressure compressor section being connected to the lower-pressure turbine section, and the higher pressure compressor section being connected to the higher-pressure turbine section, the adjacent ends of the compressor stator sections are secured to a structural member which supports a bearing for the adjacent hollow end of the rotor of the higher-pressure section, and a bearing for the adjacent end of the rotor of the lower-pressure section, the downstream end of which has a toothed connection with a sleeve carrying the inner race for the adjacent bearing, the sleeve having a splined connection with an intermediate shaft which extends through the firstmentioned bearing to the shaft of the lower-pressure turbine section and has a ball connection with the said downstream end. The rotor 33, Fig. 3, of the low-pressure compressor is connected to the shaft 43, Figs. 4 and 5, of the low-pressure turbine by means of an intermediate shaft 41 which is splined at 44 and 73 to sleeves 35 and 72 respectively. A flange 32 on the rotor 33 has a toothed connection at 34 with the sleeve 35 and a ball-and-socket connection 39, 40 with the shaft 41. Similar connections 71 and 70 are provided at the other end of the shaft 41. The rotor 46 of the high-pressure compressor is connected to the shaft 51 of the high-pressure turbine by a toothed connection 66 and a ball-and-socket connection 65. The casings 11 and 12 of the low-pressure and highpressure compressors are secured at 25, 26 to an intermediate casing member 24 which carries combined thrust and journal bearings 27, 28 which support the adjacent ends of the rotors 33, 46 through the respective flanges 34, 45. Journal bearings 59, 60 support the downstream ends of the rotor 46 and shaft 41 respectively and are supported by a diaphragm 62 which is supported from the inner casing 53 of the compressor diffuser. Shafts 43, 51 are supported by journal bearings 48, 50, respectively, and the upstream end (not shown) of rotor 33 is also supported by a journal bearing. Bearing 50 is carried by a member 52 supported from the inner casing 53. Auxiliaries are driven through bevel, gearing 29, radial shafts 30 and further bevel gearing 29, radial shafts 30 and further bevel gearing 31. The compressors are preferably provided with thrust balances 75, Figs. 3 and 4.