GB579820A - Improvements in or relating to power-gas-generators for internal-combustion power units - Google Patents

Abstract

579,820. Gas turbines. BELL, F. R., JUDSON, C. A., and HAWORTH, L. June 22, 1943, No. 10065. [Class 110 (iii)] In a gas turbine plant for jet-propulsion of aircraft, the high-pressure stage 33, Fig. 1b, of the air-compressor is carried by a tubular shaft 34 driven by the first rotor 38 of the turbine. The intermediate compressor, not shown, is carried by a second tubular shaft 41 driven by the second turbine rotor 45 and the low-pressure stage of the compressor is carried by an inner shaft 47 driven by the last two turbine rotors 53, 54. These shafts have no bearing beyond the turbines, the inner ones being carried by bearings within the next outer ones and the outermost carried by a bearing 36 in the fixed structure. Air from the compressors is delivered through guides 30 to the interior of a shell 16 and passes into combustion chambers 17. Shafts 34, 41 carry gear-teeth meshing with wheels 56, 64 which have bevel-gear connections with two rested shafts 60, 61. A starting motor can be clutched either to the shaft 60 alone or to the two shafts 60, 61. The inner shaft 47 may drive a propeller comprising a number of blades 81, Fig. 2, rotating in front of fixed blades 86 in a wind tunnel 85. The blades 81 are carried by a shell 80 fast on a short shaft 76 which is driven through epicyclic gearing 72 from the shaft 47.