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公开(公告)号：US09551238B2
公开(公告)日：2017-01-24
申请号：US13723499
申请日：2012-12-21
Applicant: United Technologies Corporation
Inventor： Hoyt Y. Chang , Shelton O. Duelm
CPC classification number: F01D25/28 , F01D25/246 , F05D2300/6033 , Y02T50/672 , Y10T403/217
Abstract: A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open.
Abstract translation: 具有第一热膨胀系数的第一物体和具有第二热膨胀系数的第二物体之间的连接器具有连接到第二物体的槽。 由具有槽形状的内壳和与第二物体的外表面共混的第一部分形成的槽，槽具有面向前的封闭部分和敞开的后部。
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公开(公告)号：US20160003072A1
公开(公告)日：2016-01-07
申请号：US14767512
申请日：2014-02-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hoyt Y. Chang , Shelton O. Duelm
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D5/282 , F01D5/284 , F05D2220/32 , F05D2230/23 , F05D2230/60 , F05D2240/12 , F05D2300/2261 , F05D2300/44 , F05D2300/6033 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a gas turbine engine has a first layer forming a cavity having transitioning from a first thickness to a second thickness through a ply drop region. A second layer is secured to the first layer.
Abstract translation: 用于燃气涡轮发动机的翼型件具有形成通过层压降区域从第一厚度过渡到第二厚度的空腔的第一层。 第二层被固定到第一层。
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公开(公告)号：US20150377045A1
公开(公告)日：2015-12-31
申请号：US14765008
申请日：2014-01-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hoyt Y. Chang , Shelton O. Duelm
IPC: F01D9/02
CPC classification number: F01D9/02 , F01D5/147 , F01D5/18 , F01D5/282 , F01D5/284 , F01D9/041 , F01D25/162 , F05D2220/32 , F05D2230/23 , F05D2230/60 , F05D2240/12 , F05D2240/121 , F05D2240/303 , F05D2300/2261 , F05D2300/44 , F05D2300/6012 , F05D2300/6033 , Y02T50/672 , Y02T50/673
Abstract: A vane assembly within a mid-turbine frame of a gas turbine engine includes an airfoil that extends between an outer platform and an inner platform. The airfoil includes an outer wall defining a leading edge of a first radius. An inner wall of the airfoil defines an inner cavity including a forward portion proximate the leading edge defining a second radius different than the first radius.
Abstract translation: 在燃气涡轮发动机的中涡轮机框架内的叶片组件包括在外平台和内平台之间延伸的翼型件。 翼型件包括限定第一半径的前缘的外壁。 翼型件的内壁限定内腔，该内腔包括靠近前缘的前部，限定不同于第一半径的第二半径。
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公开(公告)号：US20140093371A1
公开(公告)日：2014-04-03
申请号：US13630019
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tuan David Vo , Shelton O. Duelm
CPC classification number: F02C7/24 , F01D9/023 , F01D25/145 , F01D25/26 , F02C7/20 , F05D2240/14 , F05D2240/15 , F05D2260/231 , Y02T50/675
Abstract: A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.
Abstract translation: 用于中涡轮机框架的隔热罩具有锥形体，其包括至少一个轴向保持特征，至少一个周向保持特征和至少一个径向保持特征。
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公开(公告)号：US20190048744A1
公开(公告)日：2019-02-14
申请号：US16157388
申请日：2018-10-11
Applicant: United Technologies Corporation
Inventor： David J. Sander , Shelton O. Duelm
CPC classification number: F01D25/26 , F01D9/041 , F01D25/162 , F01D25/246 , F02C7/20 , F05D2220/32 , F05D2230/60 , F05D2230/642 , F05D2230/644 , F05D2240/12 , F05D2240/14 , Y02T50/672 , Y02T50/673
Abstract: A method of assembling an attachment structure of a gas turbine engine includes providing a frame that has a first annular case, an inner annular case spaced radially inwardly from the first annular case, and a plurality of vanes extending between the inner case and the first annular case, providing a second annular case that extends around the frame, the first annular case and the second annular case include a plurality of interlocks, each of the plurality of interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second annular case, and inserting the first member in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.
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Patent Agency Ranking
公开(公告)号：US10167779B2
公开(公告)日：2019-01-01
申请号：US13630019
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Tuan David Vo , Shelton O. Duelm
Abstract: A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.
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公开(公告)号：US10119423B2
公开(公告)日：2018-11-06
申请号：US14426252
申请日：2013-09-17
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Charles W. Brown , Christopher M. Quinn , Shelton O. Duelm , Peter V. Tomeo , Corey L. Hubbert
Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.
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公开(公告)号：US20140093358A1
公开(公告)日：2014-04-03
申请号：US13723499
申请日：2012-12-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hoyt Y. Chang , Shelton O. Duelm
IPC: F01D25/28
CPC classification number: F01D25/28 , F01D25/246 , F05D2300/6033 , Y02T50/672 , Y10T403/217
Abstract: A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open.
Abstract translation: 具有第一热膨胀系数的第一物体和具有第二热膨胀系数的第二物体之间的连接器具有连接到第二物体的槽。 由具有槽形状的内壳和与第二物体的外表面共混的第一部分形成的槽，槽具有面向前的封闭部分和敞开的后部。
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公开(公告)号：US20140056685A1
公开(公告)日：2014-02-27
申请号：US13590348
申请日：2012-08-21
Applicant: United Technologies Corporation
Inventor： Shelton O. Duelm , Stephanie Ernst , Eric Charles Mundell , Robert C. Stutz
CPC classification number: F01D25/08 , F01D11/00 , F01D11/02 , F02C7/24 , F02C7/28 , F05D2230/53 , F05D2240/15 , F05D2260/231 , Y02T50/675
Abstract: An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbomachine.
Abstract translation: 示例性的环形涡轮机械密封件包括附接部分，附接部分的径向内侧的第一腿部和附接部分径向向内的第二腿部，并且构造成阻止与涡轮机械的轴承室相关联的附件的直接接触的流动。
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公开(公告)号：US10774687B2
公开(公告)日：2020-09-15
申请号：US16157388
申请日：2018-10-11
Applicant: United Technologies Corporation
Inventor： David J. Sander , Shelton O. Duelm
Abstract: A method of assembling an attachment structure of a gas turbine engine includes providing a frame that has a first annular case, an inner annular case spaced radially inwardly from the first annular case, and a plurality of vanes extending between the inner case and the first annular case, providing a second annular case that extends around the frame, the first annular case and the second annular case include a plurality of interlocks, each of the plurality of interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second annular case, and inserting the first member in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.
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