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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：US20150125304A1
公开(公告)日：2015-05-07
申请号：US14203681
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon M. Rapp , Matthew Andrew Hough
CPC classification number: F01D5/22 , F01D11/008 , Y02T50/671
Abstract: A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. Adjacent platforms are separated from each other by a gap. A damper is positioned at an offset position within the gap to contact the inner surfaces of the adjacent platforms.
Abstract translation: 燃气涡轮发动机转子组件包括彼此间隔开的多个叶片以绕轴线旋转。 每个叶片包括具有内表面和外表面的平台。 相邻的平台彼此间隔开。 阻尼器位于间隙内的偏移位置处以接触相邻平台的内表面。
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Patent Agency Ranking
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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公开(公告)号：US20150369057A1
公开(公告)日：2015-12-24
申请号：US14765852
申请日：2014-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon M. Rapp , Matthew Andrew Hough
CPC classification number: F01D5/26 , F01D5/02 , F01D5/12 , F01D5/22 , F01D5/3007 , F01D5/326 , F01D11/006 , F05D2220/32 , F05D2240/55 , F05D2250/71 , F05D2250/73 , F05D2260/96
Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.
Abstract translation: 用于燃气涡轮发动机转子组件的阻尼器密封件具有带前缘，后缘，压力侧和吸力侧的轴向细长主体。 细长体包括形成在前缘的压力侧的第一扩大部分和形成在与后缘相邻的吸力侧上的第二扩大部分。
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公开(公告)号：US10036260B2
公开(公告)日：2018-07-31
申请号：US14765852
申请日：2014-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon M. Rapp , Matthew Andrew Hough
CPC classification number: F01D5/26 , F01D5/02 , F01D5/12 , F01D5/22 , F01D5/3007 , F01D5/326 , F01D11/006 , F05D2220/32 , F05D2240/55 , F05D2250/71 , F05D2250/73 , F05D2260/96
Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.
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公开(公告)号：US10012085B2
公开(公告)日：2018-07-03
申请号：US14765859
申请日：2014-03-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough , Brandon M. Rapp
CPC classification number: F01D5/10 , F01D5/26 , F01D5/3007 , F01D11/006 , F05D2260/96 , Y10T29/49323
Abstract: A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.
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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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