| 摘要 |
1,127,853. Aircraft propulsion; air cushion vehicles. ROLLS-ROYCE Ltd. 17 June, 1967, No. 28030/67. Headings B7G and B7K. [Also in Division F1] The invention relates to a gas turbine engine comprising coaxial low pressure, intermediate pressure and high pressure rotating systems each being independently rotatable and comprising an axial flow compressor and turbine drivingly interconnected. The IP compressor is arranged to compress more air than is required for the HP compressor, the excess air from the IP compressor being conveyed to a point of use. The engine shown is a gas turbine ducted fan engine and comprises LP compressor 15, IP compressor 18, HP compressor 21, combustion equipment 33, HP turbine 23, IP turbine 20 and LP turbine 17, the LP, IP and HP compressors being connected by shafts 16, 19, 22 to LP, IP and HP turbines respectively. The LP compressor is a ducted fan, part of the air discharging through a propulsion nozzle formed between the fan casing 26 and the main engine casing 28, the remaining air passing to the IP compressor 18. The IP compressor comprises an upstream portion 29 and a downstream portion 30, the upstream portion having a larger capacity than the downstream portion so that part of the air from the upstream portion passes to the annular duct 32 and is utilized externally. The air in the duct 32 passes to a duct 36 within a pylon 12 by which the engine is supported from the wing 11 of an aircraft and the air may then pass under the control of interconnected valve members 37, 41 either to the duct 38 for use in flap blowing or to the duct 39 for use in a forward propulsion nozzle 40. The air taken from the IP compressor could alternatively be used with a blown helicopter rotor for propulsion and boundary layer control; again it could be used for air cushion vehicles. |
