[특허]Composite filled gas turbine engine blade with gas film damper

[미국특허] Composite filled gas turbine engine blade with gas film damper 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/16 F01D-005/14
출원번호	US-0131570 (2005-05-18)
등록번호	US-7278830 (2007-10-09)
발명자 / 주소	Vetters,Daniel K.
출원인 / 주소	Allison Advanced Development Company, Inc.
대리인 / 주소	Krieg DeVault, LLP
인용정보	피인용 횟수 : 21 인용 특허 : 19

초록

A gas turbine engine blade comprises a housing, a composite core located within the housing, and a gas damper located within the housing for damping vibration of the blade.

대표청구항 ▼

What is claimed is: 1. A gas turbine engine airfoil comprising: a housing; a composite core located within said housing, said composite core including a fiber reinforcement portion and a matrix material portion; a gas damper located between said housing and said composite core for damping vibration of the airfoil; and wherein said housing comprises a shell and a closure, said shell defines a cavity that said composite core is located in and includes an opening into said cavity, said closure is attached to said shell and at least partially closes said opening, and said gas damper is located between said closure and said composite core. 2. The gas turbine engine airfoil of claim 1, wherein said gas damper is located in a gap defined between said composite core and said housing, and wherein said gas damper including a gas that contacts said housing and said composite core. 3. The gas turbine engine airfoil of claim 1, wherein said gas damper is an air damper, and wherein the gas turbine engine airfoil is one of a fan blade, a compressor blade and a turbine blade. 4. The gas turbine engine airfoil of claim 1, wherein said shell has a substantially open side forming said opening; wherein said composite core includes a core surface facing said opening; and wherein said closure is a closure plate attached to said shell but not to said composite core and said closure plate has an outer surface that defines a portion of an outer surface of the airfoil. 5. The gas turbine engine airfoil of claim 1, wherein the gas turbine engine airfoil defines a gas turbine engine blade. 6. A gas turbine engine airfoil comprising: a housing; a composite core located within said housing, said composite core including a fiber reinforcement portion and a matrix material portion; a gas damper located between said housing and said composite core for damping vibration of the airfoil; wherein the gas turbine engine airfoil is a blade; wherein said housing comprises a shell having a cavity that said composite core is located in and a cover member, said shell having a sidewall member with an opening therein, and said cover member connected to said shell and at least partially closing said opening; wherein said gas damper is located between said cover member and said composite core, and said gas damper including a gas that contacts a surface of said composite core and a surface of said cover member; wherein said shell and said cover member are formed of a metallic material; wherein said matrix material portion is an organic matrix material; and wherein said housing having an airfoil shaped outer surface. 7. A gas turbine engine blade comprising: a blade shell comprising an internal cavity and a side opening; a fiber-reinforced core attached to said blade shell and substantially filling said internal cavity; a sidewall member attached to said blade shell and at least partially closing said side opening, said sidewall member and said blade shell defining an outer surface including an airfoil portion; and a gas film damper located between said core and said sidewall member. 8. The gas turbine engine blade of claim 7, wherein said gas film damper is an air film damper including air located in a gap formed between said core and said sidewall member; and wherein said sidewall member is not attached to said core. 9. The gas turbine engine blade of claim 7, wherein said shell comprises a root portion, a tip portion, a leading edge portion and a trailing edge portion; wherein said root portion is integrally formed with a rotor disk; wherein said sidewall member extends in a spanwise direction between said root portion and said tip portion and in a streamwise direction between said leading edge portion and said trailing edge portion; and wherein said gas film damper is an air damper located in a gap formed between said core and said sidewall member. 10. The gas turbine engine blade of claim 7, wherein said shell comprises a root portion, a tip portion, a leading edge portion and a trailing edge portion; wherein said root portion is not integrally formed with a rotor disk; wherein said sidewall member extends in a spanwise direction between said root portion and said tip portion and in a streamwise direction between said leading edge portion and said trailing edge portion; and wherein said gas film damper is an air damper located in a gap formed between said core and said sidewall member. 11. The gas turbine engine blade of claim 7, wherein said core including an organic matrix material. 12. The gas turbine engine blade of claim 11, wherein said core includes a fiber preform embedded with said organic matrix material. 13. The gas turbine engine blade of claim 7, wherein said core is one of a fiber-reinforced aluminum matrix material core and a fiber-reinforced magnesium matrix material core. 14. The gas turbine engine of claim 7, wherein said gas film damper is an air film damper including a quantity of air located in a gap formed between said core and said sidewall member; wherein said sidewall member is not attached to said core; wherein said shell comprises a root portion, a tip portion, a leading edge portion and a trailing edge portion; wherein said sidewall member extends in a spanwise direction between said root portion and said tip portion and in a streamwise direction between said leading edge portion and said trailing edge portion; and wherein said core includes a fiber preform embedded with an organic matrix material. 15. A method of making a gas turbine engine blade, comprising: placing a fiber preform through an open side of a blade shell into an internal cavity of the blade shell; introducing a matrix material through the open side of the blade shell into the internal cavity to impregnate the fiber preform and define a composite core; creating a location for a gas film damper adjacent the composite core; attaching a sidewall member to the shell to cover at least a portion of the open side; and forming a gas film damper within the location between the core and the sidewall. 16. The method of claim 15, wherein said attaching comprises connecting the sidewall member to the blade shell but not to the core. 17. The method of claim 15, wherein said forming comprises providing a film of air spanning between the composite core and the sidewall member. 18. The method of claim 15, wherein said creating comprises making a recessed portion in the core, and said forming comprises receiving a gas within the recessed portion. 19. The method of claim 15, wherein said creating comprises removing material from the core. 20. The method of claim 15, wherein said creating comprises forming a near net shaped recessed portion in the core.

이 특허에 인용된 특허 (19) 인용/피인용 타임라인 분석

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Morrison, Jay A.; Campbell, Chris; Merrill, Gary Brian; Lane, Jay Edgar; Thompson, Daniel George; Albrecht, Harry A.; Shteyman, Yevgeniy P., Ceramic matrix composite gas turbine vane.
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Graff John M. (West Suffield CT) Violette John A. (Granby CT), Composite blade manufacture.
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Boszor Samuel M. (Palm Beach Gardens FL) Sanders Stuart A. (Palm Beach Gardens FL), Compressor blade containment with composite stator vanes.
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Rosman Irwin E. (Woodland Hills CA) Lin Jerhong (Woodland Hills CA), Fiber-composite turbine blade and method for its construction.
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Bratton Raymond J. (Delmont PA) Andersson Clarence A. (Pittsburgh PA), Method of manufacturing a transpiration cooled ceramic blade for a gas turbine.
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David William Crall, Methods and apparatus for damping rotor assembly vibrations.
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Schilling Jan C. ; Cornell Jay L. ; Stevenson Joseph T., Panel damped hybrid blade.
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Blakeley Anthony (4116 Florida Dr. Rockford IL 61108) Horihan Gregory E. (3358 Tannenbaum La. Rockford IL 61109) Konicek Timothy S. (138 Flintridge ; Apt. 5 Rockford IL 61107) O\Callaghan Patrick J. , Turbine blade with metallic attachment and method of making the same.
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Lewis, Thomas M.; Jones, David I. G., Turbine engine damper.
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McCaffrey, Michael G., Ceramic matrix composite airfoil structure with trailing edge support for a gas turbine engine.
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Jarmon, David C.; Smith, Peter G., Ceramic matrix composite combustor vane ring assembly.
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Jarmon, David C.; Butler, Shaoluo L., Gas turbine engine joint having a metallic member, a CMC member, and a ceramic key.
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Murdock, James R., Hollow fan blade tuning using distinct filler materials.
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Kirkpatrick, Bowden; Kray, Nicholas Joseph; Anderson, Todd Alan; Van Nieuwenhove, Stefaan Guido; Yeh, Po-Ching, Hybrid metal and composite spool for rotating machinery.
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Chivers, Nigel J.D.; Goldfinch, Keith C., Method of manufacturing a rotor for a gas turbine engine that includes identifying the frequency response of the rotor and adjusting the frequency response by providing a pressure gradient within the rotor.
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Merrill, Gary B.; Campbell, Christian X.; Jackson, Thomas Barrett, Processing method for solid core ceramic matrix composite airfoil.
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McCaffrey, Michael G., Turbine rotor non-metallic blade attachment.
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[미국특허] Composite filled gas turbine engine blade with gas film damper 원문보기

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[미국특허] Composite filled gas turbine engine blade with gas film damper 원문보기

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