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公开(公告)号：US10060262B2
公开(公告)日：2018-08-28
申请号：US14895139
申请日：2014-05-28
Applicant: United Technologies Corporation
Inventor： Robert Knowlton , Max Asterlin , Brandon M. Rapp , Parth Jariwala
CPC classification number: F01D5/10 , F01D5/081 , F01D5/18 , F01D5/26 , F01D11/006 , F05D2240/57 , F05D2260/96 , Y02T50/676
Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.
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Patent Agency Ranking
公开(公告)号：US20140166229A1
公开(公告)日：2014-06-19
申请号：US13719419
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert Rabinovich , Dilip M Shah , Alan D. Cetel , John Joseph Marcin , Max Asterlin
Abstract: A refractory metal core for forming internal features in a turbine engine component has a core formed from a refractory metal material; and the core has at least one blended surface on at least one edge of the core.
Abstract translation: 用于在涡轮发动机部件中形成内部特征的难熔金属芯具有由难熔金属材料形成的芯体; 并且芯在芯的至少一个边缘上具有至少一个混合表面。
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公开(公告)号：US20160102557A1
公开(公告)日：2016-04-14
申请号：US14895139
申请日：2014-05-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Robert Knowlton , Max Asterlin , Brandon M. Rapp , Parth Jariwala
CPC classification number: F01D5/10 , F01D5/081 , F01D5/18 , F01D5/26 , F01D11/006 , F05D2240/57 , F05D2260/96 , Y02T50/676
Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.
Abstract translation: 描述了涡轮叶片减振器。 阻尼器具有轴向延伸的主体，其限定内表面和相对的阻尼表面。 主体还具有从内表面到阻尼表面的边缘，并且延伸穿过主体的开槽孔。 开槽孔在内表面和阻尼表面之间延伸。 相邻的开槽孔对形成了限定纵向轴线的细长形状，该轴线在阻尼器表面的一个点处相交。
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公开(公告)号：US20160001356A1
公开(公告)日：2016-01-07
申请号：US14769803
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Max Asterlin , Jeffrey S. Beattie , John R. Gunn
CPC classification number: B22D15/00 , B22C9/10 , B22D25/02 , B22D27/04 , B22D27/045 , C30B11/00 , C30B29/52 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/041 , F02C3/04 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2260/20 , F05D2260/204 , F05D2300/607 , F05D2300/608 , Y02T50/676
Abstract: A cast component includes a cast body that has a single crystal microstructure and an internal corner bounding an internal cavity. The single crystal microstructure defines a critical internal residual stress with respect to investment casting of the cast body using a refractory metal core beyond which the single crystal microstructure recrystallizes under a predetermined condition. The internal corner has a corner radius that is greater than a critical corner radius below which an amount of internal residual stress in the single crystal microstructure exceeds the critical internal residual stress. The internal cavity includes a cross section less than about 20 mils near the corner radius.
Abstract translation: 铸造组件包括具有单晶微结构的铸造体和包围内腔的内角。 单晶微结构定义了使用难熔金属芯相对于铸造体的熔模铸造的关键内部残余应力，超临界内的单晶微结构在预定条件下重结晶。 内角具有大于临界角半径的角半径，低于该半径时，单晶微结构中的内部残余应力的量超过临界内部残余应力。 内腔包括在拐角半径附近小于约20密耳的横截面。
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公开(公告)号：US10227875B2
公开(公告)日：2019-03-12
申请号：US14766190
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Scott D. Lewis , Brandon M. Rapp , Jeffrey S. Beattie , Matthew Andrew Hough , Bret M. Teller , Jeffrey Michael Jacques , Max Asterlin
IPC: F01D5/18 , F01D11/08 , F23R3/00 , F23R3/04 , F01D9/06 , F01D25/12 , F23R3/06 , F01D9/02 , F23R3/02
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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公开(公告)号：US10226814B2
公开(公告)日：2019-03-12
申请号：US14769803
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Max Asterlin , Jeffrey S. Beattie , John R. Gunn
IPC: B22D15/00 , B22D27/04 , B22C9/10 , C30B29/52 , B22D25/02 , F01D5/18 , F01D9/04 , C30B11/00 , F01D5/28 , F02C3/04
Abstract: A cast component includes a cast body that has a single crystal microstructure and an internal corner bounding an internal cavity. The single crystal microstructure defines a critical internal residual stress with respect to investment casting of the cast body using a refractory metal core beyond which the single crystal microstructure recrystallizes under a predetermined condition. The internal corner has a corner radius that is greater than a critical corner radius below which an amount of internal residual stress in the single crystal microstructure exceeds the critical internal residual stress. The internal cavity includes a cross section less than about 20 mils near the corner radius.
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