[특허]Gas turbine engine buffer system providing zoned ventilation

Gas turbine engine buffer system providing zoned ventilation 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-006/08 F01D-005/08 F01D-025/16 F01D-025/18 F02C-007/18
출원번호	US-0366450 (2012-02-06)
등록번호	US-10018116 (2018-07-10)
발명자 / 주소	Ackermann, William K. Stripinis, Philip S.
출원인 / 주소	UNITED TECHNOLOGIES CORPORATION
대리인 / 주소	Carlson, Gaskey & Olds
인용정보	피인용 횟수 : 0 인용 특허 : 34

초록

A gas turbine engine includes a first zone and a second zone downstream from the first zone. A buffer system can communicate a buffer cooling air to at least the first zone. A bleed source can communicate a bleed air to the second zone.

대표청구항 ▼

1. A gas turbine engine, comprising: a compressor section;a combustor in fluid communication with said compressor section;a turbine section in fluid communication with said combustor;an inner shaft that interconnects a first portion of said compressor section and a first portion of said turbine section;an outer shaft that interconnects a second portion of said compressor section and a second portion of said turbine section;a bearing structure that supports said inner shaft and said outer shaft, wherein said bearing structure defines a bearing compartment;a disk bore seal that divides said compressor section into a first zone and a second zone, said disk bore seal positioned between a bore of a disk of said compressor section and said outer shaft;a buffer system including a heat exchanger or an ejector configured to condition a bleed air supply and communicate a buffer cooling air to said bearing structure and to said first zone, wherein a first portion of said buffer cooling air is communicated within said first zone at a location radially outward of said outer shaft to ventilate said disk and a second portion of said buffer cooling air is communicated between said outer shaft and said inner shaft, and wherein said disk bore seal blocks said first portion of said buffer cooling air from entering said second zone but does not block said second portion of said buffer cooling air from being communicated between said outer shaft and said inner shaft;a bleed source located within said second zone and configured to communicate a bleed air to ventilate said second zone;a port configured to receive said bleed air from said bleed source and communicate said bleed air into said second zone; andan anti-vortex tube in fluid communication with said port and configured to direct the bleed air radially inwardly toward said outer shaft. 2. The gas turbine engine as recited in claim 1, wherein said buffer system includes a first bleed air supply, a second bleed air supply, and a valve configured to select between said first bleed air supply and said second bleed air supply to communicate said buffer cooling air to said first zone. 3. The gas turbine engine as recited in claim 2, wherein said first bleed air supply is communicated as said buffer cooling air in response to high power conditions of the gas turbine engine and said second bleed air supply is communicated as said buffer cooling air in response to low power conditions of the gas turbine engine. 4. The gas turbine engine as recited in claim 3, wherein said high power conditions include takeoff, climb, and cruise conditions of the gas turbine engine. 5. The gas turbine engine as recited in claim 3, wherein said low power conditions include ground operation, ground idle, and descent idle conditions of the gas turbine engine. 6. The gas turbine engine as recited in claim 1, comprising a controller programmed to command the actuation of said buffer cooling air in response to detecting a flight condition of the gas turbine engine. 7. The gas turbine engine as recited in claim 6, comprising a sensor configured to detect said flight condition. 8. The gas turbine engine as recited in claim 6, wherein said controller is configured to generate a signal to command operation of said heat exchanger or said ejector in response to detecting said flight condition. 9. The gas turbine engine as recited in claim 1, wherein said bleed air is a different source of air than said buffer cooling air. 10. The gas turbine engine as recited in claim 1, wherein the gas turbine engine is a high bypass geared aircraft engine that includes a fan and a geared architecture, wherein the geared architecture is configured to control the fan at lower speeds than said inner shaft.

이 특허에 인용된 특허 (34)

Weiner Harvey I. (South Windsor CT) Allard Kenneth L. (Wilbraham MA), Active clearance control.
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Lee Ching-Pang (Cincinnati OH) Carlson Clay K. (Cincinnati OH) Shelton Monty L. (Cincinnati OH) Rieck ; Jr. Harold P. (West Chester OH) Mason Harvey W. (Loveland OH) Hauser Ambrose A. (Wyoming OH), Aft entry cooling system and method for an aircraft engine.
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Mortzheim, Jason Paul; Zhou, Ming; Marks, Paul Thomas, Apparatus and methods for controlling flow in turbomachinery.
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Taylor Michael C. (Chellaston GB3), Arrangement for supplying cooling air to a turbine casing of an aircraft gas turbine.
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Fish,Jason Araan; L챕gar챕,Pierre Yves; Hawie,Eduardo David, Bearing chamber pressurization system.
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Smith Stanley (Gloucestershire GB2), Bearing chamber pressurization system for a machine.
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Stevens Leonard W. (Vernon CT) Siwik William S. (Manchester CT) Moore William A. (Durham CT) Brown Wayne M. (North Granby CT) Barnard Andrew A. (Glastonbury CT), Bearing compartment protection system.
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Forrester, James Michael; Bolt, Janine Elizabeth; Rhoda, James Edwin; Stevenson, Joseph Timothy, Circular arc multi-bore fan disk.
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Lenahan Dean Thomas (Cincinnati OH) Pedersen Poul D. (Cincinnati OH) Plemmons Larry Wayne (Fairfield OH) Glynn Christopher Charles (Hamilton OH) Miller Frederick M. (Cincinnati OH) Stover Curtis W. (, Compressor rotor cooling system for a gas turbine.
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Eveker Kevin M. ; Gysling Daniel L. ; Nett Carl N. ; Wang Hua O., Compressor stall and surge control using airflow asymmetry measurement.
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Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E., Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor.
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Perry Derick A. (Derby), Deicing of a geared gas turbine engine.
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Coffinberry George A. (West Chester OH), Gas turbine engine cooling system.
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Walker,Herbert L.; Akerley,Stevan W., Gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger.
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Barcza William K. (Palm City FL), Gas turbine nose cone attachment.
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Bock, Alexander, Gas-turbine engine with a bearing chamber.
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Mortimer, Thomas P.; Suciu, Gabriel L., Heat exchange system.
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Farris Edsel S. (Burton WA), Jet flow deflector for aircraft.
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Girault Daniel G. (Melun FRX), Lubricating and cooling system for intershaft bearing of turbojet.
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Rocklin, Mark; Karvountzi, Georgia C.; Hummel, Daniel S., Method and apparatus for aircraft anti-icing.
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Hovan Edward J. (Manchester CT), Method of operation for a gas turbine engine.
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Honkomp,Mark Steven; Barrett,Joseph Scott, Methods and apparatus for assembling gas turbine engine rotor assemblies.
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Benjamin,Edward Durell; Butkiewicz,Jeffrey John; Urban,John Paul, Methods and apparatus for cooling gas turbine engine rotor assemblies.
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Asselin Jean-Claude (Moret Sur Loing FRX) Glowacki Pierre A. (Fontaine Le Port FRX), Nose cowl for a turbojet engine shaft.
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Pope Adam N. (Cincinnati OH) Hwang Ming-Fong (West Chester OH), System and method for improved engine cooling in conjunction with an improved gas bearing face seal assembly.
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Earith, Thomas Julien Roland; Picart, Jean-Yves, System for deicing an aircraft turbine engine inlet cone.
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Goodman Robert B. (West Hartford CT), Temperature control system.
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Brodell Robert F. (Marlborough CT) Laurello Vincent P. (Guilford CT), Thrust balancing and cooling system.
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Quinones Armando J. (Cincinnati OH) Rieck ; Jr. Harold P. (West Chester OH) Albrecht Richard W. (Fairfield OH) Sullivan Michael A. (Ballston Spa NY) Weisgerber Robert H. (Loveland OH) Plemmons Larry , Turbine disk cooling system.
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Suciu,Gabriel L.; Norris,James W., Turbine engine rotor stack.
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Suciu,Gabriel L.; Norris,James W., Turbine engine rotor stack.
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Liu Xiaoliu,CAX, Turbine engine with cooled P3 air to impeller rear cavity.
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Xavier Gerard Andre Coudray FR; Mischael Fran.cedilla.ois Louis Derrien FR; Marc Roger Marchi FR; Philippe Christian Pellier FR; Jean-Claude Christian Taillant FR; Thierry Henri Marcel Tassin , Turbomachine including a device for supplying pressurized gas.
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Hein,Stefan; Stein,Manuela; Peitsch,Dieter, Vortex reducer in the high-pressure compressor of a gas turbine.
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Gas turbine engine buffer system providing zoned ventilation 원문보기

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Gas turbine engine buffer system providing zoned ventilation 원문보기

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