| 摘要 |
626,044. Gas turbines; centrifugal compressors. BRISTOL AEROPLANE CO., Ltd., OWNER, F. M., and MARCHANT, F. C. I. June 21, 1945, No. 15879. [Classes 110(i) and 110(iii)] A two stage back-to-back centrifugal compressor delivers air to four obliquely disposed helical combustion chambers 12 and the products of combustion are delivered with a tangential component to quadrantal nozzle conduits 26 which unite to form a complete annular entry to the turbine 11. The turbine comprises two rotors .one of which is mounted on the airscrew shaft 15 and the other, on a tubular shaft carrying the two compressor rotors. The low-pressure compressor takes air from an annular inlet 13 and delivers it from its volute to four conduits 23 which turn the air from the tangential to a radially inward direction and bring it to the inlet of the high-pressure stage. The discharge from the latter stage is taken tangentially from the volute and led to the combustion chambers by conduits 24 which lie under the conduits 23. |
