IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0271695
(2002-10-15)
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발명자
/ 주소 |
- Eiler, Donald C.
- Larkin, Michael J.
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출원인 / 주소 |
- United Technologies Corporation
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
10 인용 특허 :
6 |
초록
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The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the
The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the turbine and the fan and thereby generating additional thrust for the aircraft. The engine is also used to provide power to one or more systems onboard the aircraft.
대표청구항
▼
1. A variable boost cycle propulsor system for a vehicle comprising:an engine; a turbine mounted within a casing; a bypass passageway formed between an inner surface of a fuselage of said vehicle and an outer surface of said casing; a fan driven by said turbine, said fan being positioned within said
1. A variable boost cycle propulsor system for a vehicle comprising:an engine; a turbine mounted within a casing; a bypass passageway formed between an inner surface of a fuselage of said vehicle and an outer surface of said casing; a fan driven by said turbine, said fan being positioned within said bypass passageway; and means for selectively delivering a fluid output from said engine to said turbine for selectively creating thrust. 2. The variable boost cycle propulsor system according to claim 1, further comprising said engine being embedded within said fuselage of said vehicle and an air inlet passageway within said fuselage to deliver air to an inlet of said engine.3. The variable boost cycle propulsor system according to claim 1, further comprising means for delivering air to said bypass passageway when said system is in a boost thrust mode.4. The variable boost cycle propulsor system according to claim 1, wherein said selective delivery means comprises a passageway for delivering said fluid output from said engine to said turbine and a valve positioned within said passageway and said valve being movable between a first position where said fluid output is directed overboard via an outlet nozzle and a second position where the fluid output is directed to the turbine so as to rotate said fan and create a propulsive force.5. The variable boost cycle propulsor system according to claim 4, wherein said valve is a rotatable gate valve.6. The variable boost cycle propulsor system according to claim 4, wherein fluid exiting said fan mixes with said fluid output of said engine in an exit nozzle to create a propulsive force.7. The variable boost cycle propulsor system according to claim 1, further comprising means for supplying power from said engine to at least one aircraft system.8. The variable boost cycle propulsor system according to claim 7, wherein said engine has a compressor, a turbine, and a shaft connecting said compressor and said turbine and said power supplying means comprises a mechanical connection for taking power off said shaft and delivering said power to said at least one aircraft system.9. The variable boost cycle propulsor system according to claim 7, wherein said engine has a compressor and said power supplying means comprises pneumatic power supplying means.10. A variable boost cycle propulsor system for a vehicle comprising:an engine; a turbine; a fan driven by said turbine; means for selectively delivering a fluid output from said engine to said turbine for selectively creating thrust; a bypass passageway formed between an inner surface of said fuselage and an outer surface of said casing and said fan being positioned within said bypass passageway; and said bypass passageway communicating with an exit nozzle and an axially movable plug for closing said exit nozzle when said system is in a non-boost thrust mode. 11. A variable boost cycle propulsor system for a vehicle comprising:and engine; a turbine; a fan driven by said turbine; means for selectively delivering a fluid output from said engine to said turbine for selectively creating thrust; means for delivering air to said bypass passageway when said system is in a boost thrust model and said air delivering means comprising an air inlet in said fuselage and an inlet flap connected to said fuselage and movable between an open position and a closed position. 12. An aircraft having a fuselage and a variable boost cycle propulsor system embedded within a portion of said fuselage, and said variable boost cycle propulsor system including an engine embedded within said fuselage, a turbine embedded within said fuselage and being located within a casing, a bypass passageway between an inner surface of said fuselage and an outer surface of said casing, a fan connected to said turbine, said fan being positioned within said bypass passageway, and means for delivering a fluid output from said engine to drive said turbine and said fan and thereby create additional thrust for said aircraft.13. An aircraft according to claim 12, wherein said variable boost cycle propulsor system is embedded within a tail portion of said fuselage.14. An aircraft according to claim 12, wherein said fluid output delivering means includes a fluid passageway extending between said engine and said turbine and a valve within said fluid passageway movable between a first position where said fluid output is delivered to said turbine and a second position where said fluid output is exhausted overboard.15. An aircraft according to claim 12, further comprising means for delivering air to said bypass passageway.16. An aircraft according to claim 12, further comprising an exit nozzle for receiving fluid exiting the fan and fluid exiting the turbine.17. An aircraft having a variable boost cycle propulsor system embedded within a portion of said fuselage, and said variable boost cycle propulsor system including an engine embedded within said fuselage, a turbine embedded within said fuselage, a fan connected to said turbine, means for delivering a fluid output from said engine to drive said turbine and said fan and thereby create additional thrust for said aircraft, said fluid output delivering means including a fluid passageway extending between said engine and said turbine, a valve within said fluid passageway movable between a first position where said fluid output is delivered to said turbine and a second position where said fluid output is exhausted overboard, said turbine being positioned within a casing, a bypass passageway between an inner surface of said fuselage and an outer surface of said casing, said fan being positioned within said bypass passageway, an exit nozzle communicating with said bypass passageway and an axially movable plug for closing said exit nozzle when said variable boost cycle propulsor system is in a non-boost mode.18. An aircraft having a variable boost cycle propulsor system embedded within a portion of said fuselage, and said variable boost cycle propulsor system including an engine embedded within said fuselage, a turbine embedded within said fuselage, a fan connected to said turbine, means for delivering a fluid output from said engine to drive said turbine and said fan and thereby create additional thrust for said aircraft, said fluid output delivering means including a fluid passageway extending between said engine and said turbine, a valve within said fluid passageway movable between a first position where said fluid output is delivered to said turbine and a second position where said fluid output is exhausted overboard, said turbine being positioned within a casing, a bypass passageway between an inner surface of said fuselage and an outer surface of said casing, said fan being positioned within said bypass passageway, means for delivering air to said bypass passageway, said air delivering means comprises an inlet in said fuselage and a flap movable between a first position where air is introduced into said inlet and a second position for preventing air from entering said bypass passageway.
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