[특허]Multi-nozzle flow diverter for jet engine

Multi-nozzle flow diverter for jet engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/077 F02K-003/02 F02K-003/075 F02C-006/08 F02K-003/06 F02K-001/82
출원번호	US-0888967 (2013-05-07)
등록번호	US-9920710 (2018-03-20)
발명자 / 주소	Dawson, David Lynn Lariviere, Erin Lee Petersen, Brian Joseph Ellerhorst, Robert Jerome
출원인 / 주소	General Electric Company
대리인 / 주소	General Electric Company
인용정보	피인용 횟수 : 0 인용 특허 : 33

초록 ▼

An exhaust system for a variable cycle aircraft engine. The exhaust system comprises a core exhaust for bypass air and hot gases of combustion. The core exhaust includes a convergent-divergent nozzle. The convergent-divergent nozzle is formed from a plurality of flaps and seals. The exhaust system comprises a third air duct for a third stream of air. The third stream of air is selectively exhausted from the third duct through a secondary nozzle or divergent slots in the convergent-divergent nozzle, or both depending upon the flight mode. A diverter valve is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the divergent slots and combinations thereof.

대표청구항 ▼

1. An aircraft turbofan engine, having a fan portion providing three streams of air flow to the aircraft turbofan engine, comprising: an engine core receiving core air flow that is exhausted through a primary nozzle;a bypass duct receiving bypass air flow; anda third air duct receiving third stream air flow, the third stream airflow flowing through the third air duct, the third air duct having an air inlet and an air outlet, the air outlet of the third air duct further comprising a secondary nozzle, the primary nozzle and a flow diverter valve to direct the third stream air flow to at least one of the secondary nozzle or the primary nozzle, wherein the secondary nozzle is positioned to direct the third stream air flow over outer flaps of the primary nozzle. 2. The aircraft turbofan engine of claim 1 wherein the air outlet for third stream airflow that includes the primary nozzle further includes fluid communication between the flow diverter valve along divergent slots formed in divergent flaps and seals in the primary nozzle. 3. The aircraft turbofan engine of claim 1 wherein the flow diverter valve is a passive valve. 4. The aircraft turbofan engine of claim 3 wherein the flow diverter valve is biased into a first position by a pressure of the third stream air flow in the third air duct to provide fluid communication to the primary nozzle and to the secondary nozzle. 5. The aircraft turbofan engine of claim 4 wherein the flow of third stream air to the primary nozzle further provides cooling to divergent flaps and seals in the primary nozzle. 6. The aircraft turbofan engine of claim 3 wherein the flow diverter valve biases to a second position overcoming a pressure of the third stream air flow in the third air duct to block fluid communication between the third air duct and the primary nozzle, directing third stream air flow to the secondary nozzle only. 7. The aircraft turbofan engine of claim 6 wherein the flow diverter valve biases to the second position that blocks a backflow of hot gases from the primary nozzle into the third air duct. 8. The aircraft turbofan engine of claim 1 wherein the flow diverter valve is an active valve. 9. The aircraft turbofan engine of claim 8 wherein the flow diverter valve is in communication with a controller that determines and controls the position of the flow diverter valve. 10. The aircraft turbofan engine of claim 9 wherein the third air duct further includes pressure sensors monitoring an air pressure in communication with the controller. 11. The aircraft turbofan engine of claim 10 wherein the controller determines a first position of the flow diverter valve providing fluid communication to both the secondary nozzle and the primary nozzle when the air pressure within the third air duct exceeds a predetermined pressure. 12. The aircraft turbofan engine of claim 10 wherein the controller determines a second position of the flow diverter valve providing fluid communication to the secondary nozzle while blocking fluid communication to the primary nozzle when the air pressure within the third air duct is at or below a predetermined pressure. 13. The aircraft turbofan engine of claim 8 wherein the flow diverter valve is in communication with an engine FADEC. 14. The aircraft turbofan engine of claim 13 wherein the engine FADEC determines the position of the flow diverter valve based on operating conditions of the aircraft turbofan engine. 15. The aircraft turbofan engine of claim 1 wherein a pressure and temperature of the third stream air flow in the third air duct is at a lower pressure and temperature than a pressure and temperature of the bypass air flow. 16. The aircraft turbofan engine of claim 1 wherein the third stream air flow provided to the third air duct is from the fan portion of the aircraft turbofan engine fore of bypass air. 17. The aircraft turbofan engine of claim 1 wherein third stream air flow is provided to the third air duct by a blade-on-fan or FLADE™, the third stream air flow in the third air duct being sealed from the core air flow and the bypass air flow. 18. The aircraft turbofan engine of claim 1 wherein the flow diverter valve is located within the third air duct adjacent to primary nozzle cross section A7, where A7 is the cross-sectional area at an upstream end of convergent flaps and seals.

이 특허에 인용된 특허 (33)

Carey John P. (Upper Marlboro MD) Lee Robert (Cincinnati OH) Majjigi Rudramuni K. (Cincinnati OH), Acoustically shielded exhaust system for high thrust jet engines.
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Kepler Charles E. (Manchester CT), Air turbo-ramjet engine.
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Banthin ; Clifford R., Apparatus for and method of suppressing infrared radiation emitted from gas turbine engine.
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Salemann Victor (Issaquah WA), Bypass duct for a hypersonic propulsion system.
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Rabone George R. (Cincinnati OH), Convergent-divergent plug nozzle.
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Neitzel Robert E. (Marblehead MA), Convertible aircraft engine.
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Smale Charles H. (Indianapolis IN) Pyne ; Jr. James A. (Phoenix AZ), Cooled exhaust duct.
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Powell, Brandon Flowers; Decker, John Jared, Double bypass turbofan.
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Wadia, Aspi Rustom; Turner, Alan Glen; Dziech, Aaron Michael; Szucs, Peter Nicholas; Decker, John Jared, FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween.
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Johnson ; Joseph M., Gas turbine exhaust nozzle for controlled temperature flow across adjoining airfoils.
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Lahti Daniel J. (Cincinnati OH) Yates David E. (Cincinnati OH) Mungur Parmanand (West Chester OH) Stockman Norbert O. (Batavia OH), Hybrid laminar flow nacelle.
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Amelio Armand F. (Yonkers NY) Rosen Kenneth M. (Guilford CT), Infra-red suppressor for use with turbo-shaft engine.
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Hurley John F. (Huntington CT) Banthin Clifford R. (Redding CT), Infrared radiation suppressor for a gas turbine engine.
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Ross Thomas D. (West Palm Beach FL) Owen Samuel S. (Jupiter FL), Infrared suppressor.
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Mouritsen Thorvald E. (Dallas TX) Simpkin William E. (Dallas TX), Infrared suppressor device.
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Dusa Donald J. (Cincinnati OH), Multiple bypass-duct turbofan with annular flow plug nozzle and method of operating same.
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Stockman Norbert O. (Batavia OH) Yates David E. (Cincinnati OH) Crum Timothy S. (Fairfield OH), Nacelle inlet for an aircraft gas turbine engine.
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Roth, Bryce Alexander, Operating line control of a compression system with flow recirculation.
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Siedlecki ; Jr. Walter F. (West Chester OH), Passive bypass valve assembly.
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Johnson Douglas (Indianapolis IN), Radiation suppression.
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Johnson James E. (Hamilton OH), Spillage drag and infrared reducing flade engine.
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Johnson James E. (Hamilton OH), Spillage drag reducing flade engine.
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Simmons John Robert (Cincinnati OH), Split fan work gas turbine engine.
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Schaut ; Larry Allen ; Zimbrick ; Richard Alan, Stator bypass system for turbofan engine.
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Janardan, Bangalore Ananthamurthy; Brausch, John Francis, Stub airfoil exhaust nozzle.
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Baughman,John Lewis; Johnson,James Edward, Thrust vectoring aft FLADE engine.
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Johnson, James E., Turbine engine with modulated flow fan and method of operation.
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Giffin ; III Rollin G. ; Johnson James E. ; Crall David W. ; Salvage John W. ; Szucs Peter N., Turbofan engine with a core driven supercharged bypass duct.
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Wynosky Thomas A. (Madison CT) Campbell Charles A. (Palm Beach Gardens FL) Mischke Robert J. (Middletown CT), Two-dimensional plug nozzle.
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Thomas William W. (Cincinnati OH) Sprunger Elmore V. (Cincinnati OH), Two-spool variable cycle engine.
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Johnson James Edward (Hamilton OH) Foster Tom (Cincinnati OH) Allan Roy Duncan (Cincinnati OH), Variable cycle gas turbine engines.
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Rundell ; Dan Joseph ; McHugh ; Donald Patrick ; Foster ; Tom ; Brown ; Ralph Harold, Variable mixer propulsion cycle.
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Giffin ; III Rollin G. (Cincinnati OH), Variable specific thrust turbofan engine.
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