| 摘要 |
955,014. Gas turbine jet propulsion plant. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Feb. 6,1962 [Feb. 6,1961], No. 4486/62. Headings F1G and F1J. A jet engine is provided with a duct containing a turbine 9, Fig. 2 driving a compressor 7 delivering air into a conduit 14 which debouches externally of the duct, a conduit 38 for by-passing a gas turbine unit 11, an additional combustion chamber 33 arranged upstream of turbine 9 and a switching device 29 for directing the airstream flowing through the duct either toward the gas turbine unit or toward the by-pass and thence to the additional combustion chamber. The jet engine is in the configuration of Fig. 2 for operation at low flight speeds with the jack-operated switching device 29 arranged to uncover the gas turbine inlet conduit 37 and to cover by-pass 38 while a jack-operated valve 30 covers the inlet port in the combustion chamber. Air in conduit 36 is compressed by compressor 11 and burnt in chamber 13, the combustion gases being expanded first in a turbine 10, then in turbine 9 and in nozzle 3 through which they are ejected. After-burning may be provided in the chamber 33. In the upper range of flight speeds the engine is arranged in the configuration of Fig. 3 in which the gas generator conduit is closed and the by-pass 38 is opened into chamber 33. Air in conduit 36 which has been highly compressed in the intake supplies chamber 33 and the combustion gases are expanded in turbine 9 and then in nozzle 3, the gas generator rotor 12 being halted. The air in conduit 14, Fig. 1 is lead to a low-pressure compressor in a known arrangement of compound jet engine in which ducts 1, 2, which may be wholly or partly separated, terminate in separate convergent-divergent variable geometry nozzles 3 and 4 having a common or variable geometry intakes 5 and 6. Compressor 7, delivers air via conduit 14, valve 15 into a combustion chamber 16 which supplies a turbine 17. The turbine 17 is coupled by shaft 18 to a low pressure compressor 19 provided with means 24 for changing the angle of fixed bladings 25, 26. Air passing through annular duct 20 is heated at 27 and after mixing with gases from turbine 17 may be reheated at 22. Specification 955,013 is referred to. |
