[특허]Thermal management system integrated pylon

Thermal management system integrated pylon 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/02 F02K-099/00 F02C-006/08 F02K-003/06 F02C-007/14 F02C-007/18 B64D-033/10 B64D-027/18 F02C-007/224 F02K-003/115 B64D-029/00
출원번호	US-0020728 (2008-01-28)
등록번호	US-8826641 (2014-09-09)
발명자 / 주소	Suciu, Gabriel L. Merry, Brian D. Dye, Christopher M.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 33

초록 ▼

A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placemen

대표청구항 ▼

1. A thermal management system for a gas turbine engine comprising: a bifurcation area;at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine, said at least one heat exchanger positioned downstream of a fan strut, said fan strut spanning between a core nacelle of said gas turbine engine and a fan nacelle of said gas turbine engine;wherein said at least one heat exchanger includes first and second heat exchangers, said first and second heat exchangers mounted within a common plenum defined by said bifurcation area to share a common inlet; andwherein first and second exits are formed, in part, by a split in the plenum downstream of said inlet. 2. The system as recited in claim 1, wherein said bifurcation area is at least partially within a pylon structure. 3. The system as recited in claim 1, wherein said bifurcation area is forward of a pylon structure. 4. The system as recited in claim 1, wherein said bifurcation area is at least partially within a bifurcation. 5. The system as recited in claim 1, wherein said at least one heat exchanger is mounted at least partially within a pylon structure. 6. The system as recited in claim 1, wherein said at least one heat exchanger is mounted at least partially within an upper bifurcation. 7. The system as recited in claim 1, wherein said at least one heat exchanger is mounted forward of a pylon structure. 8. The system as recited in claim 3, wherein said at least one heat exchanger is mounted at least partially within an upper bifurcation. 9. The system as recited in claim 1, wherein at least one flow vane is positioned on one side of said split, downstream of one of said first and second heat exchangers, leading to one of said first and second exits. 10. The system as recited in claim 9, wherein said at least one flow vane includes a plurality of flow vanes, including a modulated flow vane to modulate an exit airflow. 11. The system as recited in claim 1, wherein said first and second heat exchangers are positioned on opposite sides of said split in said plenum. 12. The system as recited in claim 1, wherein said first and second heat exchangers are separate heat exchangers, and are spaced apart from one another. 13. A thermal management system for a gas turbine engine comprising: a bifurcation area;at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine;wherein said at least one heat exchanger comprises a first heat exchanger and a second heat exchanger, said at least one heat exchanger positioned entirely downstream of an outlet of a fan case and a fan strut, said fan strut spanning between a core nacelle of said gas turbine engine and a fan nacelle of said gas turbine engine. 14. The system as recited in claim 13, wherein said first heat exchanger and said second heat exchanger are mounted within a common plenum defined by said bifurcation area to share a common inlet. 15. A thermal management system for a gas turbine engine comprising: a bifurcation area;at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine;wherein said at least one heat exchanger comprises a first heat exchanger and a second heat exchanger;wherein said first heat exchanger and said second heat exchanger are mounted within separate plenums on either side of a central inlet guide vane defined by said bifurcation area, said first heat exchanger and said second heat exchanger each being positioned downstream of a fan strut, said fan strut spanning between a core nacelle of said gas turbine engine and a fan nacelle of said gas turbine engine; andwherein said central inlet guide vane defines a first inlet for said first heat exchanger and a second inlet for said second heat exchanger. 16. The system as recited in claim 15, wherein said first heat exchanger and said second heat exchanger communicate through a respective first and second exit. 17. The system as recited in claim 15, wherein said central inlet guide vane is spaced downstream of a fan section of the gas turbine engine. 18. A thermal management system for a gas turbine engine comprising: a bifurcation area;at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine, said at least one heat exchanger positioned downstream of a fan strut, said fan strut spanning between a core nacelle of said as turbine engine and a fan nacelle of said gas turbine engine; andwherein said at least one heat exchanger is positioned entirely downstream of a fan case of said gas turbine engine.

이 특허에 인용된 특허 (33)

Fournier, Alain; Laboure, Bernard, Aeroengine nacelle afterbodies.
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Glickstein Marvin R. (North Palm Beach FL), Aircraft cooling method.
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Monhardt Richard J. (Glastonbury CT) Kudlacik Louis (Glastonbury CT) Nikkanen John P. (West Hartford CT) Niiler Juri (Glastonbury CT), Combined surge bleed and dust removal system for a fan-jet engine.
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Proctor Robert ; Epstein Michael J. ; Fraser Gordon G. ; Farley Scott E. ; Koch Richard F. ; Siebert Robert W., External cooling system for turbine frame.
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Reuter, Charles; Dyer, Gerald P.; Haugsjaahabink, Todd; Shah, Satish, Fluid flow system for a gas turbine engine.
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Macfarlane,Ian; Szlanta,Zenon; Mitrovic,Lazar; Morgan,Keith, Gas turbine engine architecture.
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Vermejan Alexander E. (Mason OH) Daiber Paul C. (Cincinnati OH) Morton Scott C. (Cincinnati OH) Taylor Michelle L. (Cincinnati OH), Gas turbine engine fan cooled heat exchanger.
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Czachor,Robert Paul, Gas turbine engine frame having struts connected to rings with morse pins.
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Parsons Franklin D. (Cincinnati OH), Heat exchange arrangement in a gas turbine engine fan duct for cooling hot bleed air.
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Glickstein Marvin R. (North Palm Beach FL) Dixon James T. (Jupiter FL) Podolsky Donald M. (Jupiter FL), High pressure air source for aircraft and engine requirements.
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Glickstein Marvin R. (North Palm Beach FL) Dixon James T. (Jupiter FL) Podolsky Donald M. (Jupiter FL), High pressure air source for aircraft and engine requirements.
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Dixon James T. (Jupiter FL) Glickstein Marvin R. (North Palm Beach FL), Integrated auxiliary power system.
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Moorehead James R. (Bellevue WA), Integrated power plant installation system.
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George E. Wilmot, Jr. ; Gregory M. Ott, Integrated thermal management and coolant system for an aircraft.
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Durocher,Eric; Pietrobon,John Walter, Lightweight annular interturbine duct.
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Weber Kent, Method and apparatus for rejecting waste heat from a system including a combustion engine.
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Udall, Kenneth F, Mounting arrangement for a gas turbine engine.
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Miller Franklin E. (Cincinnati OH), Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine.
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Huang, He; Kaslusky, Scott F.; Tillman, Thomas G.; DeValve, Timothy D.; Bertuccioli, Luca; Sahm, Michael K.; Spadaccini, Louis J.; Bayt, Robert L.; Lamm, Foster Philip; Sabatino, Daniel R., System and method for thermal management.
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John Alan Manteiga ; Christopher James Wilusz ; Cornelius Harm Dykhuizen, System for mounting aircraft engines.
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Niggemann Richard E. ; Nguyen Dam, Thermal and energy management method and apparatus for an aircraft.
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Sabatino,Daniel; Spadaccini,Louis J.; Kaslusky,Scott, Thermal management system for an aircraft.
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Meisels,David, Turbine shroud cooling system.
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Rolt,Andrew M, Turbofan arrangement.
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Lillibridge Robert W. ; McGuire Kenneth R. ; Phillips Edward J. ; Matthews Eugene James, Turbofan engine with reduced noise.
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Miller Franklin E. (Cincinnati OH), Turbojet cooling system.
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