A turbofan engine is provided with a conventional air by-pass duct communicating with a plenum chamber downstream of the engine core, vectoring nozzles upstream of the by-pass duct, and a non-vectoring nozzle and a jet-pipe exhausting from the plenum chamber. In conventional forward thrust mode the
A turbofan engine is provided with a conventional air by-pass duct communicating with a plenum chamber downstream of the engine core, vectoring nozzles upstream of the by-pass duct, and a non-vectoring nozzle and a jet-pipe exhausting from the plenum chamber. In conventional forward thrust mode the two sets of nozzles are closed and the jet-pipe is open. In lift thrust mode the jet-pipe is closed and the two sets of nozzles are open, the non-vectoring nozzle providing vertical thrust. The closure member for the vectoring nozzle is arranged, when open, to divert turbofan air to the vectoring nozzles which would otherwise have passed along the by-pass duct, and to divert to the vectoring nozzles exhaust gases from the plenum chamber that are constrained to flow in reverse along the by-pass duct. The non-vectoring nozzle is sized to permit a suitable split between gases exhausting there through and gases reverse flowing along the by-pass duct.
대표청구항▼
[ I claim:] [1.] A dual mode gas turbine jet engine including an engine casing, a turbofan, an engine core, a bypass duct between the engine casing and the engine core, and a jet-pipe, wherein there is further provided at least one first jet nozzle located downstream of the turbofan and upstream of
[ I claim:] [1.] A dual mode gas turbine jet engine including an engine casing, a turbofan, an engine core, a bypass duct between the engine casing and the engine core, and a jet-pipe, wherein there is further provided at least one first jet nozzle located downstream of the turbofan and upstream of the engine core providing communication between the bypass duct and the ambient atmosphere, a second jet nozzle located downstream of the engine core and upstream of the jet-pipe providing communication between a plenum chamber downstream of the engine core and the ambient atmosphere, and first, second, third and fourth closure means to close off respectively the at least one first jet nozzle, the bypass duct, the second jet nozzle, and the jet-pipe, the arrangement of the respective closure means being that, in a first mode of operation, of the at least one first jet nozzle and the second jet nozzle at least the second jet nozzle is closed, the bypass duct is open to air from the turbofan, and the jet-pipe is open, whereby the engine operates in a conventional forward thrust mode; and, in a second mode of operation, the jet-pipe is closed, the at least one first jet nozzle and the second jet nozzle are open, and the bypass duct is closed to air from the turbofan but operates in reverse flow to direct gases from the plenum chamber to the at least one first nozzle, whereby the engine is capable of operating in a lift thrust mode.
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이 특허를 인용한 특허 (5)
Chang, Stanley, Air compression type engine for aviation.
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