Patent GB-590422-A (GB)
Title: Improvements in and relating to power plants
IPC: F02C3/08
Filed: 1945-03-07
Abstract: 590,422. Gas turbines. BRITISH THOMSON-HOUSTON CO., Ltd. March 7, 1945, No. 5732. Convention date, March 7, 1944. [Class 110 (iii)] [Also in Group XXXIII] A gas turbine assembly for the jet propulsion of aircraft is built up of four sections each being an integral assembly complete in itself. The four are : an auxiliaries section 10, Fig. 2, a compressor section 11, a combustion chamber and turbine section 12, and a turbine exhaust section 13. Two such turbines are mounted in casings 4 on opposite sides of the fuselage 1 of an aeroplane and are fitted with jet tubes 265. The double-entry centrifugal compressor rotor 15, Fig. 8, is mounted in a ballbearing 22 and a rollerbearing 32. Fine adjustment of axial position is provided for by mounting the outer ball-race in a sleeve 28, the projecting portion of which is threaded into an adjusting nut 29. The diffusor is divided by vanes 45, Fig. 9, into as many parts as there are combustion chambers and each part ends with a series of guides 54 which turn the flow into an axial direction. Tubes 63, Fig. 8, convey the compressed-air to the combustion chambers and carry combustion domes 75 and burners 76. These tubes are secured to the combustion chambers and to facilitate removal, distance pieces 65 are located between the tubes and the diffusor flanges 53. The bell-shaped structures 23, 33 which carry the bearings and the inlet guide surfaces 67 are braced by struts 59 between the flanges 24, 34 and 48, 49. The turbine rotor 80, Fig. 11, is overhung on a shaft 83 which is mounted in a ball-bearing 84 and a roller bearing 85. The ball-bearing is adjustable axially by means of a threaded sleeve 99 and nut 102. The bell-shaped structure carrying the bearings is braced by integral struts 89 and ties 150 between the flange 91 and the nozzle ring 121. The compressor is driven through a sleeve 172 which has straight splines 174 engaging the crowned splines 36 on the trunnion 20 and curved splines to embrace the crowned splines 97 on the turbine shaft. The outer walls 129 of the combustion chambers are shaped, at their delivery ends, to fit together and form a complete annulus. They are united by rings 121, 123. The liners 132 have perforations 133 for admitting the combustion air. They are positioned by ribs 134 and anchored by bolts 136. The outer walls are united by open tube pieces and through these pass tubes 171 which interconnect the liner spaces. Air from the compressor inlet passes between the struts 89 and through passages 114 to the turbine rotor face and is pumped out by blades 117 on the rotor and diffusor blades 116. The exhaust section comprises a double outer wall 189, 175 and an inner wall 177 of a sugar loaf shape. Bracing tubes 178 are encased by streamlined farings 181. The section carries a heat shield 186. The framework of the auxiliaries section, Fig. 5, comprises a casing 200 with an end wall 202 and flange 201 and two discs 204, 205 supported in the casing. Suitable gears for driving various auxiliaries from the tubular shaft 208 are mounted in the discs 204, 205. A starting motor 220 drives through a pinion 220a, a spur wheel 219 on shaft 217 and an overrunning clutch 218. A starting fuel pump is driven from the spur wheel 219. Specification 590,418 is referred to.