| 摘要 |
1,146,347. Gas turbine engines. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec.1, 1966 [Dec. 2, 1965], No.53826/66. Headings F1G and F1T. A gas turbine engine comprises a contrarotating compressor having two coaxial rotors the blades of which are disposed alternately in sequence, the two rotors being driven by two turbine rotor stages, the turbine rotor stages having stator guide vanes associated therewith and there being means for varying the cross-sectional area of the fluid-flow passages through the guide vane assemblies. In the embodiment shown, the compressor comprises an outer rotor drum 3 carrying blades 1, and an inner rotor carrying blades 2, the outer drum 3 being driven by a turbine stage 14 through shaft 4, and the inner rotor being driven by two turbine stages 15 and 16 through shaft 6. Inlet nozzle guide vanes 17, 18, 19 are associated with the turbine stages 14, 15, 16 respectively and means are provided for varying the cross-sectional area of the fluid-flow passages between the guide vanes. In one embodiment the guide vanes are angularly adjustable for this purpose, while in a second embodiment the guide vanes are hollow and are provided with slots in the concave surface, fluid under pressure being supplied to the space within each guide vane, the fluid discharging through the slot. |
