[특허]Method of sizing and forming a cooling hole in a gas turbine engine component

[미국특허] Method of sizing and forming a cooling hole in a gas turbine engine component 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B21D-053/78
출원번호	US-0684987 (2000-08-29)
발명자 / 주소	Gary Eugene Wheat Terri Kay Brown Thomas Phillip Schumacher
출원인 / 주소	General Electric Company
대리인 / 주소	Andrew C. Hess
인용정보	피인용 횟수 : 13 인용 특허 : 9

초록 ▼

A method for accurately sizing and forming the cooling holes of an air-cooled gas turbine engine component on which a protective diffusion coating will be deposited. The method generally entails drilling a hole in a surface region of a substrate, and then measuring the thickness of any recast surface region surrounding the hole and created as a result of a portion of the surface region having melted and then resolidified. The thickness of the additive layer of the diffusion coating that will deposit on a corresponding recast surface region of the component is then predicted based on an inverse relationship determined to exist with the thickness of the recast surface region formed during drilling of the cooling hole. An appropriately-oversized hole can then be formed in the component so that, after depositing the diffusion coating on the component, the additive layer grows sufficiently within the hole to yield a cooling hole approximately having the required final diameter.

대표청구항 ▼

1. A method of sizing and forming a cooling hole in a gas turbine engine component, the method comprising the steps of:forming a hole in a surface region of a substrate; measuring the thickness of any recast surface region surrounding the hole and created during the forming step as a result of the forming step having caused a portion of the surface region to melt and then resolidify; obtaining a gas turbine engine component having a surface region in which a cooling hole having a desired diameter is to be formed and on which will be deposited a diffusion coating comprising a diffusion zone that will extend into the surface region of the component and an additive layer that will deposit on the surface region of the component at a growth rate determined by a first set of deposition parameters; predicting a thickness of the additive layer of the diffusion coating on the component based on an inverse relationship between the thickness of the recast surface region of the substrate and the growth rate of the additive layer; forming a hole in the surface region of the component, the hole having a formed diameter that is larger than the desired diameter of the cooling hole; and then depositing the diffusion coating on the surface region of the component so that the additive layer grows sufficiently at the hole to yield the cooling hole approximately having the desired diameter.

이 특허에 인용된 특허 (9) 인용/피인용 타임라인 분석

Fleck James N., Co-machined bonded airfoil.
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Marriage Peter V. (Derby GB2), Cooled turbomachinery components.
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Turner Stephen C.,GB3, Laser barrier material and method.
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Lozier Todd B. (Hamilton OH) Kelley James G. (California KY), Method and apparatus for laser trepanning.
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Gupta Bhupendra K. ; Ziegler Robert P. ; Scheidt Wilbur D., Method for making a fluid cooled article with protective coating.
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Wilkinson Bernard H. (Skipton GB2) Meleka Abdou H. (Bristol GB2) Glew Derek A. (Bristol GB2), Methods and apparatus for electrically machining a work piece.
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Kikkawa Shouichi (Takasago JPX) Takahashi Kouji (Takasago JPX) Aoki Sunao (Takasago JPX), Process for manufacturing a gas turbine blade.
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Fernihough John,CHX ; Beeck Alexander,DEX ; Bogli Andreas,CHX, Process of plugging cooling holes of a gas turbine component.
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Kildea Robert J., Tip seal and anti-contamination for turbine blades.
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이 특허를 인용한 특허 (13) 인용/피인용 타임라인 분석

Caldwell,James Michael; Tomlinson,Thomas John; Zimmerman, Jr.,Robert George; Heidorn,Raymond William; Farmer,Gilbert, Adjusting airflow in turbine component by depositing overlay metallic coating.
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Beddard,Thomas B.; Collado,Carlos A., Airfoil cooling holes.
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Steele, David, Cooling method and apparatus.
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Joslin, Frederick R., Leak resistant vane cluster.
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Fernihough, John; Oehl, Markus, Method of adjusting the size of cooling holes of a gas turbine component.
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Dean, Gilbert Joseph; Williams, David; Parks, Kenneth Lorenzo; Kyano, Rachel Elizabeth; Baker, Benjamin Erick; Kuang, Hui, Method of forming a trailing edge cutback for a turbine bucket.
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Fleck, James N., Method of making turbulated cooling holes.
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Paauwe,Corneil; Devore,Matthew, Method of producing cooling holes in highly contoured airfoils.
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Das,Nripendra Nath; Rigney,Joseph David; Pfaendtner,Jeffrey Allan; Saylor,Matthew David, Method of selective region vapor phase aluminizing.
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Rizzo, Jr., John P.; Barron, Alan C., Methods for creating a film cooled article for a gas turbine engine.
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Bezdecny, Michelle Rene; Graham, Michael Evans; Bartholomew, Michael Lee, Methods for testing turbine blades.
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Bunker, Ronald Scott; Wei, Bin; Ritter, Ann Melinda; Lipkin, Don Mark; Rebak, Raul Basilio; Kool, Lawrence Bernard; Gray, Dennis Michael, Turbine components with cooling features and methods of manufacturing the same.
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Fleck, James N., Turbulated cooling holes.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Method of sizing and forming a cooling hole in a gas turbine engine component 원문보기