[특허]Methods and apparatus for maintaining rotor assembly tip clearances

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-006/08 F02C-006/00
출원번호	US-0925465 (2004-08-25)
등록번호	US-7269955 (2007-09-18)
발명자 / 주소	Albers,Robert Joseph Ruiz,Rafael Boyle,Marcia Glynn,Christopher Charles
출원인 / 주소	General Electric Company
대리인 / 주소	Armstrong Teasdale LLP
인용정보	피인용 횟수 : 10 인용 특허 : 39

초록 ▼

A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the airflow in the heat exchanger, an

A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the airflow in the heat exchanger, and directing the cooled airflow into the engine casing to cool the casing.

대표청구항 ▼

What is claimed is: 1. A method of operating a gas turbine engine, the gas turbine engine comprising at least one engine casing, and at least one rotor assembly, said method comprising: directing airflow through a supply pipe from at least one of a fan, a booster, and a compressor into a heat excha

What is claimed is: 1. A method of operating a gas turbine engine, the gas turbine engine comprising at least one engine casing, and at least one rotor assembly, said method comprising: directing airflow through a supply pipe from at least one of a fan, a booster, and a compressor into a heat exchanger; lowering the temperature of the airflow in the heat exchanger; directing the cooled airflow into the engine casing to cool the casing; and directing at least a portion of the airflow to the heat exchanger to be cooled and reused. 2. A method in accordance with claim 1 wherein said gas turbine engine further comprises a high pressure aft cavity and a high pressure turbine disk, said method further comprising: directing the cooled airflow to the high pressure aft cavity; and cooling an aft surface of the high pressure turbine disk. 3. A method in accordance with claim 1 wherein the heat exchanger comprises a coolant loop, said method further comprising directing at least a portion of the gas turbine engine fuel through the heat exchanger coolant loop to cool the airflow in the heat exchanger. 4. A clearance control system for a gas turbine engine, the gas turbine engine comprising a fan, a compressor having at least one stage and a discharge, a booster, a high pressure turbine having a least one disk, and at least one engine casing extending circumferentially around the compressor and high pressure turbine, said clearance control system comprising: an air supply pipe configured to direct air from at least one of the fan, the booster, and the compressor to the high pressure turbine; and a heat exchanger in flow communication with said air supply pipe to cool an airflow passing through said air supply pipe wherein said air supply pipe is connected to the engine casing to direct a cooling airflow inside the casing to cool the casing, said system is configured to direct the cooling airflow back to said heat exchanger to be re-cooled and reused. 5. A clearance control system in accordance with claim 4 wherein said heat exchanger comprises a coolant loop. 6. A clearance control system in accordance with claim 5 wherein said coolant loop comprises a portion of a gas turbine engine fuel line. 7. A clearance control system in accordance with claim 4 wherein the air supply pipe is coupled to the compressor discharge. 8. A clearance control system in accordance with claim 4 wherein said air supply pipe is connected to at least one of the fan, the booster, and a stage of the compressor. 9. A clearance control system in accordance with claim 4 wherein said system is configured to direct said cooling airflow to the high pressure turbine disk to cool the disk. 10. A gas turbine engine comprising: a compressor; a high pressure turbine; an engine casing extending circumferentially around said compressor and high pressure turbine said casing comprising a cooling air inlet; and a clearance control system comprising: an air supply pipe coupled to said casing cooling air inlet wherein said air supply pipe is configured to direct air from at least one of a fan, a booster, and said compressor to said high pressure turbine; and a heat exchanger coupled to and in flow communication with said air supply pipe to cool an airflow in said air supply pipe wherein said air supply pipe is connected to said engine casing to direct a cooling airflow inside the casing to cool said casing, said system is configured to direct the cooling airflow back to said heat exchanger to be re-cooled and reused. 11. A gas turbine engine in accordance with claim 10 wherein said heat exchanger comprises a coolant loop. 12. A gas turbine engine in accordance with claim 11 wherein said coolant loop comprises a portion of a gas turbine engine fuel line. 13. A gas turbine engine in accordance with claim 12 wherein said cooling air inlet is located in said casing to direct a cooling airflow inside said casing to cool said casing. 14. A gas turbine engine in accordance with claim 10 wherein said air supply pipe is coupled to said compressor discharge. 15. A gas turbine engine in accordance with claim 10 further comprising a fan and a booster, said air supply pipe connected to at least one of said fan, said booster, and a stage of said compressor. 16. A gas turbine engine in accordance with claim 13 wherein said clearance control system is configured to direct said cooling airflow to said high pressure turbine disk to cool said disk.

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이 특허에 인용된 특허 (39) 인용/피인용 타임라인 분석

Davison Samuel H. (Loveland OH) Kast Kevin H. (Cincinnati OH) Clark Aidan W. (Blue Ash OH), Active clearance control.
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Albrecht Richard W. (Fairfield OH) Shepherd Andrew (Fairfield OH), Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud.
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Griffin James G. (West Hartford CT) McHale Robert J. (Manchester CT) Dreisbach ; Jr. Raymond A. (Old Saybrook CT) Beck John P. (South Windsor CT), Balancing the heat flow between components associated with a gas turbine engine.
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Cline Larry D. (Fairfield OH) Hauser Ambrose A. (Wyoming OH) Sidenstick James E. (Cincinnati OH) Zlatic Mark S. (West Chester OH), Clearance control.
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Davison Samuel H. (Milford OH) McGreehan William F. (Westchester OH), Clearance control system.
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McGreehan William F. (Westchester OH), Clearance control system.
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Lenahan Dean T. (Cincinnati OH) Shotts L. D. (Cincinnati OH) Shetty Bandadi S. (West Chester OH) Glover Jeffrey (Cincinnati OH), Clearance control system for separately expanding or contracting individual portions of an annular shroud.
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Orlando Robert J., Compressor system and methods for reducing cooling airflow.
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Proctor Robert (West Chester OH) Linger David R. (Cincinnati OH) Di Salle David A. (West Chester OH) Brassfield Steven R. (Cincinnati OH) Plemmons Larry W. (Fairfield OH), Controlled leakage shroud panel.
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Mazeaud Georges (Yerres FRX) Mirville Francois J. P. (Melun FRX) Saillot Patrick W. R. (Vaux Le Penil FRX), Cooling system for a gas turbine.
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Porte Alain,FRX, Device for bleeding off and cooling hot air in an aircraft engine.
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Proctor, Robert; Montgomery, Julius John; Epstein, Michael Jay; Barbe, Roger Owen; Sam, Hai Buu; Ogzewalla, James Bernar; Kemp, Andrew David; Doloresco, Bryan Keith, Gas turbine engine bleed scoops.
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Plemmons Larry W. (Fairfield OH) Proctor Robert (West Chester OH) Albers Robert J. (Park Hills KY) Gardner Donald L. (West Chester OH), Gas turbine engine case counterflow thermal control.
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Damlis Nicholas (Cincinnati OH) Zegarski Frederick J. (Cincinnati OH) Brayton Donald D. (Maineville OH), Gas turbine engine clearance control apparatus.
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Coffinberry George A. (West Chester OH), Gas turbine engine cooling system.
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Palmisano,Laurent; Jablonski,Laurent, Heat exchanger on a turbine cooling circuit.
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Stuart Alan R. (Hamilton OH), Intercooled turbine blade cooling air feed system.
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Ciokajlo John J. (Cincinnati OH) Hauser Ambrose A. (Cincinnati OH), Mechanical blade tip clearance control apparatus for a gas turbine engine.
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Mark Joseph Mielke ; John Jared Decker, Method and apparatus for reducing rotor assembly circumferential rim stress.
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Koch Carl C. (Cincinnati OH) Castells Onofre T. (Cincinnati OH), Method and apparatus for turbine cooling.
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David E. Bulman ; Kenneth E. Seitzer ; Craig P. Burns ; Jeffrey D. Clements, Methods and apparatus for directing airflow to a compressor bore.
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Scott Richard Zearbaugh ; Steven Louis Brickner ; James Warren Hackler ; Lonnie Ray Chadwell, Methods and apparatus for maintaining rotor assembly tip clearances.
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Proctor, Robert; Hanify, John William; Prikkel, Debra Lynn; Epstein, Michael Jay; Montgomery, Julius John, Methods and apparatus for regulating turbine clearance control system airflow.
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Griffiths, James Alan; Smith, Mitchell Donald; Bartos, James William, Methods and apparatus for supplying cooling air to turbine engines.
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Little, David Allen, Part load blade tip clearance control.
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Janes Clarence W. (Sacramento CA), Performance enhanced gas turbine powerplants.
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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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Giffin, III, Rollin G., Pressure boosted compressor cooling system.
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Mielke, Mark J.; Rhoda, James E.; Bulman, David E.; Burns, Craig P.; Smith, Paul M.; Suffoletta, Daniel G.; Ballman, Steven M.; Zylka, Richard P.; Egan, Lawrence J., Reduced-stress compressor blisk flowpath.
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Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell and bucket tip clearance control.
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Sexton Brendan F. (Clifton Park NY) Knuijt Hans M. (Niskayuna NY) Eldrid Sacheverel Q. (Saratoga Springs NY) Myers Albert (Amsterdam NY) Coneybeer Kyle E. (Schenectady NY) Johnson David Martin (Balls, Removable inner turbine shell with bucket tip clearance control.
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Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell with bucket tip clearance control.
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Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell with bucket tip clearance control.
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Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell with bucket tip clearance control.
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Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell with bucket tip clearance control.
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Coffinberry George A. ; Leonard Gary L., System and method of providing clean filtered cooling air to a hot portion of a gas turbine engine.
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Fukue Ichiro,JPX ; Akita Eiji,JPX ; Tomita Yasuoki,JPX, System for cooling blades in a gas turbine.
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Glover Jeffrey (Cincinnati OH), Tip clearance control apparatus and method.
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Walker Alan (Wyoming OH) Wakeman Thomas G. (Lawrenceburg IN) Lenahan Dean T. (Cincinnati OH) Plemmons Larry W. (Fairfield OH) Elovic Andrew P. (Rishon Lezion ILX), Turbine shroud clearance control assembly.
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Takahashi, Tatsuji; Hagi, Naoki; Ai, Toshishige, Gas turbine plant.
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Ballard, Jr., Henry G.; Beadie, Douglas Frank; Memmer, John David, Method and apparatus for clearance control utilizing fuel heating.
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Ballard, Jr., Henry Grady; Bozkurt, Ozgur; Black, Kenneth Damon; Danescu, Radu Ioan, Method and apparatus to improve heat transfer in turbine sections of gas turbines.
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Chatelois, Bruno; Bouchard, Guy; Martin, Yves, Rotor containment structure for gas turbine engine.
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Ballard, Jr., Henry G.; Wilson, Ian David; Chieco, Stephen Christopher; Kneeland, Andrew Ray; Miller, Bradley James; Black, Kenneth David; Goetze, Raymond, Systems and methods of reducing heat loss from a gas turbine during shutdown.
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Laurello, Vincent P.; Tham, Kok-Mun, Vane carrier temperature control system in a gas turbine engine.
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[미국특허] Methods and apparatus for maintaining rotor assembly tip clearances 원문보기

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[미국특허] Methods and apparatus for maintaining rotor assembly tip clearances 원문보기

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