AIRCRAFT

摘要

1,212,875. Aircraft power plant. ROLLSROYCE Ltd. 19 Dec., 1968 [21 Dec., 1967], No. 58059/67. Heading B7G. [Also in Division F1] The invention relates to an aircraft which has at least one main forward propulsion engine and an auxiliary gas turbine engine, the auxiliary engine being capable of operating in two modes, the first mode being one in which the engine produces forward thrust and the second mode being one in which the engine drives equipment to provide aircraft services independently of the main engine. A propulsion nozzle is provided for flow of exhaust gases from the auxiliary engine when operating to produce forward thrust. A shaft is provided for driving aircraft equipment from the auxiliary engine. Means are provided for silencing the intake of the auxiliary engine when it is operating in the second mode, and further means are provided for silencing the exhaust gas discharge from the auxiliary engine when it is operating in the second mode. The aircraft shown has two forward propulsion engines 2 and a single auxiliary gas turbine engine 3 which is mounted in the rear part of the fuselage. The auxiliary engine has two air intake ducts 6 and a propulsion nozzle 10 also an exhaust gas outlet 9 located at the top of the fuselage. A pivotally mounted flap member 12 is provided which may be positioned to block the outlet 9 when the engine is producing forward thrust or to block the propulsion nozzle 10 when the engine is driving the aircraft auxiliaries. A series of splitters 11 formed of sound absorbing material are located in the exhaust gas outlet. A series of splitters 16 are disposed in each of the intake ducts 6, the splitters being made of sound absorbing material. The shaft of the auxiliary engine is extended by means of a coupling 20 and shaft 21 to drive a gear-box 24 through a clutch 23. Aircraft auxiliaries such as an air compressor 27 and generator 25 are driven from the gear-box. The splitters in the air intakes may be retracta,ble as indicated in Fig. 4. The splitters are shown in the operative position at the lower part of the Figure and in the retracted, inoperative position in full lines at the upper part of the Figure; the splitters may be moved to close off the intake opening as shown in chain-dotted lines at the upper part of the Figure. The splitters may be connected together by a lazytongs linkage. Each intako duct such as 6 in Fig. 1 may have two inlet openings, one opening being unobstructed and being used when the auxiliary engine is pro u ing forward thrust, and the other opening being provided with silencing splitters and being lined with sound absorbing material, this opening being used when the auxiliary engine is driving aircraft auxiliaries.