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公开(公告)号：US10215031B2
公开(公告)日：2019-02-26
申请号：US14769600
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jaime G. Ghigliotty , Edward F. Pietraszkiewicz , Dominic J. Mongillo, Jr. , Christopher Corcoran
Abstract: A gas turbine engine component includes first and second walls spaced apart from one another to provide a cooling passage. First and second trip strips are respectively provided on the first and second walls and arranged to face one another. The first and second trip strips are arranged in an interleaved fashion with respect to one another in a direction.
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公开(公告)号：US20190032501A1
公开(公告)日：2019-01-31
申请号：US15664355
申请日：2017-07-31
Applicant: United Technologies Corporation
Inventor： Christopher Corcoran , Nicholas W. Oren , Robert L. Hazzard
Abstract: An assembly is provided for rotational equipment. This assembly includes a rotor disk, an annular arm, an annular air seal and an annular seal land. The rotor disk is rotatable about an axis. The annular arm is connected to the rotor disk. The annular arm projects axially out from the rotor disk to a distal arm end. The annular air seal is removably attached to and substantially completely supported by the annular arm at the distal arm end. The annular seal land is sealingly engaged with the annular air seal.
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公开(公告)号：US10161258B2
公开(公告)日：2018-12-25
申请号：US15071485
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin , Peter Balawajder , Christopher Corcoran
Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides with the radially outer side including radially-extending sidewalls. A radially inner surface joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A rail shield has radially-extending walls lines the radially-extending sidewalls.
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公开(公告)号：US10156144B2
公开(公告)日：2018-12-18
申请号：US14871456
申请日：2015-09-30
Applicant: United Technologies Corporation
Inventor： San Quach , Steven Bruce Gautschi , Matthew A. Devore , Scott D. Lewis , Matthew S. Gleiner , Christopher King , Christopher Corcoran , David Donald Chapdelaine
Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.
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公开(公告)号：US10125613B2
公开(公告)日：2018-11-13
申请号：US14650090
申请日：2013-12-17
Applicant: United Technologies Corporation
Inventor： Eric S. Savage , Christopher Corcoran
Abstract: A method includes determining a vibration characteristic of a shrouded turbine blade, which includes an airfoil attached to a shroud. A corner of the shrouded turbine blade can be removed after determining the vibration characteristic.
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Patent Agency Ranking
公开(公告)号：US10053992B2
公开(公告)日：2018-08-21
申请号：US14790231
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： San Quach , Scott D. Lewis , Steven Bruce Gautschi , Christopher King , Christopher Corcoran , David Donald Chapdelaine
CPC classification number: F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.
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公开(公告)号：US20180058236A1
公开(公告)日：2018-03-01
申请号：US15244203
申请日：2016-08-23
Applicant: United Technologies Corporation
Inventor： Anton G. Banks , Christopher Corcoran , Bryan P. Dube
Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.
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公开(公告)号：US20160222809A1
公开(公告)日：2016-08-04
申请号：US15021945
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough , Christopher Corcoran , Jeffrey S. Beattie
IPC: F01D11/00
CPC classification number: F01D11/006 , F01D5/22 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/75 , F05D2260/22141
Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.
Abstract translation: 燃气涡轮发动机包括涡轮部分。 涡轮机部分包括可围绕轴线旋转的盘。 多个涡轮机叶片围绕盘的周边安装，并且多个密封件布置在涡轮机叶片与盘周边之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。
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39.发明申请公开(公告)号：US20160003055A1
公开(公告)日：2016-01-07
申请号：US14769600
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jaime G. Ghigliotty , Edward F. Pietraszkiewicz , Dominic J. Mongillo, JR. , Christopher Corcoran
IPC: F01D5/18
CPC classification number: F01D5/186 , B22C9/10 , B22D25/02 , F01D5/187 , F05D2220/32 , F05D2230/30 , F05D2240/303 , F05D2240/304 , F05D2250/185 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A gas turbine engine component includes first and second walls spaced apart from one another to provide a cooling passage. First and second trip strips are respectively provided on the first and second walls and arranged to face one another. The first and second trip strips are arranged in an interleaved fashion with respect to one another in a direction.
Abstract translation: 燃气涡轮发动机部件包括彼此间隔开的第一和第二壁，以提供冷却通道。 第一和第二跳闸带分别设置在第一和第二壁上并且被布置成彼此面对。 第一和第二跳闸带在交叉方式相对于彼此沿一个方向布置。
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公开(公告)号：US20150315918A1
公开(公告)日：2015-11-05
申请号：US14650090
申请日：2013-12-17
Applicant: United Technologies Corporation
Inventor： Eric S. Savage , Christopher Corcoran
CPC classification number: F01D5/16 , F01D5/147 , F01D5/225 , F01D5/26 , F01D25/06 , F05D2220/32 , F05D2230/10 , F05D2260/96 , F05D2260/961 , Y10T29/49337
Abstract: A method includes determining a vibration characteristic of a shrouded turbine blade, which includes an airfoil attacked to a shroud. A corner of the shrouded turbine blade can be removed after determining the vibration characteristic.
Abstract translation: 一种方法包括确定包覆的涡轮叶片的振动特性，其包括攻击到护罩的翼型件。 在确定振动特性后，可以拆下带盖涡轮叶片的一角。
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