[특허]Airfoil with powder damper

United Technologies Corporation

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특허 상세정보

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Airfoil with powder damper

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/14 B21D-053/78 F01D-005/16 F01D-005/26 F01D-025/06
출원번호	US-0454440 (2012-04-24)
등록번호	US-9181806 (2015-11-10)
발명자 / 주소	Propheter-Hinckley, Tracy A. Dolansky, Gregory M. Fisk, Benjamin T. Treen, Robert J.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 2 인용 특허 : 18

초록

An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.

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1. An airfoil comprising: an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining at least one longitudinally elongated cavity in the airfoil body, at least one longitudinally elongated cavity is adjacent a cooling passage; anda plurality of loose particles enclosed in the at least one longitudinally elongated cavity. 2. The airfoil as recited in claim 1, wherein the at least one longitudinally elongated cavity is adjacent the leading edge. 3. The airfoil as recited in claim 1, wherein the at least one longitudinally elongated cavity is adjacent the trailing end. 4. The airfoil as recited in claim 1, wherein the airfoil body extends over a span from a base at a platform to a tip end, and the at least one longitudinally elongated cavity is contained within 50% of the span. 5. An airfoil comprising: an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining at least one longitudinally elongated cavity in the airfoil body, at least one longitudinally elongated cavity is adjacent a cooling passage; anda plurality of loose particles enclosed in the at least one longitudinally elongated cavity, wherein the airfoil body extends over a span from a base at a platform to a tip end, with the base being at 0% of the span and the tip being at 100% of the span, and the at least one longitudinally elongated cavity is contained within 50% of the span. 6. The airfoil as recited in claim 1, wherein the at least one longitudinally elongated cavity includes a plurality of longitudinally elongated cavities that are laterally spaced apart from each other with regard to the longitudinal axis. 7. The airfoil as recited in claim 5, wherein the the at least one longitudinally elongated cavity is contained within a middle 50% of the chord dimension. 8. The airfoil as recited in claim 1, wherein the at least one longitudinally elongated cavity is located between cooling passages. 9. The airfoil as recited in claim 1, wherein the plurality of loose particles include at least a bi-modal size distribution. 10. The airfoil as recited in claim 1, wherein the plurality of loose particles include a uni-modal size distribution. 11. The airfoil as recited in claim 1, wherein the airfoil body, exclusive of the at least one longitudinally elongated cavity, is solid. 12. The airfoil as recited in claim 1, wherein the plurality of loose particles occupy from 99.9 volume percent to 80 volume percent of the at least one longitudinally elongated cavity. 13. The airfoil as recited in claim 1, wherein the plurality of loose particles serve as a vibrational damper in the airfoil body and are formed of a powdered metal left in the at least one longitudinally elongated cavity from fabrication of the airfoil body. 14. A turbine engine comprising: optionally, a fan;a compressor section;a combustor in fluid communication with the compressor section; anda turbine section in fluid communication with the combustor, the turbine section being coupled to drive the compressor section and the fan, andat least one of the fan, the compressor section and the turbine section including an airfoil having an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining at least one longitudinally elongated cavity in the airfoil body, at least one longitudinally elongated cavity is adjacent a cooling passage, and a plurality of loose particles are enclosed in the at least one longitudinally elongated cavity. 15. The turbine engine as recited in claim 14, wherein the airfoil body extends over a span from a base at a platform to a tip end, and the at least one longitudinally elongated cavity is contained with 50 percent of the span. 16. The turbine engine as recited in claim 14, wherein the airfoil body extends over a span from a base at a platform to a tip end, with the base being at 0% of the span and the tip end being at 100% of the span, the at least one longitudinally elongated cavity is contained between 0% span and 50% span. 17. The turbine engine as recited in claim 14, wherein the at least one longitudinally elongated cavity includes a plurality of longitudinally elongated cavities that are laterally spaced apart from each other with regard to the longitudinal axis. 18. The turbine engine as recited in claim 14, wherein the airfoil body defines a chord dimension extending between the leading edge and the trailing edge, and the at least one longitudinally elongated cavity is contained within a middle 50% of the chord dimension. 19. The turbine engine as recited in claim 14, wherein the plurality of loose particles include at least a bi-modal size distribution. 20. The turbine engine as recited in claim 14, wherein the airfoil body, exclusive of the at least one longitudinally elongated cavity, is solid. 21. A method for processing an airfoil, the method comprising: depositing multiple layers of a powdered metal onto one another;joining the layers to one another with reference to data relating to a particular cross-section of an airfoil; andproducing the airfoil with an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining at least one longitudinally elongated cavity in the airfoil body, at least one longitudinally elongated cavity is adjacent a cooling passage and a plurality of loose particles enclosed in the at least one longitudinally elongated cavity. 22. The airfoil as recited in claim 5, wherein the at least one longitudinally elongated cavity is contained between 0% span and 50% span. 23. The airfoil as recited in claim 5, wherein the at least one longitudinally elongated cavity includes a plurality of longitudinally elongated cavities that are laterally spaced apart from each other with regard to the longitudinal axis. 24. The airfoil as recited in claim 5, wherein the loose particles are made of the same material as the airfoil body. 25. The airfoil as recited in claim 5, wherein the plurality of loose particles serve as a vibrational damper in the airfoil body and are formed of a powdered metal left in the at least one longitudinally elongated cavity from fabrication of the airfoil body.

이 특허에 인용된 특허 (18)

이 특허를 인용한 특허 피인용횟수: 2

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Airfoil with powder damper

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Airfoil with powder damper

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