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公开(公告)号：US20170306774A1
公开(公告)日：2017-10-26
申请号：US15134758
申请日：2016-04-21
摘要： An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall.
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公开(公告)号：US20180328224A1
公开(公告)日：2018-11-15
申请号：US15590512
申请日：2017-05-09
CPC分类号： F01D5/189 , F05D2250/21 , F05D2260/201 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： An airfoil including a leading edge, a trailing edge, a pressure side, a suction side, and an internal impingement cavity. An impingement insert is located within the impingement cavity. The impingement insert includes at least one impingement cooling hole spaced along a first face of the impingement insert and at least one impingement fin, having a base and a tip opposite the base, spaced along the first face of the impingement insert. The at least one impingement fin is spaced apart from the at least one impingement cooling hole.
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公开(公告)号：US20180030837A1
公开(公告)日：2018-02-01
申请号：US15219804
申请日：2016-07-26
发明人： Sandip DUTTA , Benjamin Paul LACY , Gary Michael ITZEL , Joseph Anthony WEBER , David Edward SCHICK
CPC分类号： F01D5/189 , B22F3/1055 , B22F5/04 , B33Y80/00 , F01D9/041 , F01D25/12 , F05D2230/22 , F05D2230/232 , F05D2230/30 , F05D2240/128 , F05D2240/30 , F05D2250/292 , F05D2260/201 , F05D2260/202 , F05D2300/171 , Y02P10/295
摘要： Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.
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