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公开(公告)号：US20190316481A1
公开(公告)日：2019-10-17
申请号：US15955590
申请日：2018-04-17
Applicant: United Technologies Corporation
Inventor： Kevin L. Rugg , Winston Gregory Smiddy
Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.
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公开(公告)号：US10385774B2
公开(公告)日：2019-08-20
申请号：US15268713
申请日：2016-09-19
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Tania Bhatia Kashyap , Mark F. Zelesky , Arthur W. Utay , Gabriel L. Suciu , Thomas N. Slavens , Kevin L. Rugg , Brian Merry
Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.
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公开(公告)号：US20180023576A1
公开(公告)日：2018-01-25
申请号：US15218915
申请日：2016-07-25
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Arthur W. Utay , Tania Bhatia Kashyap , Thomas N. Slavens , Kevin L. Rugg , Mark F. Zelesky , Brian D. Merry , Gabriel L. Suciu
CPC classification number: B64D41/00 , F02C3/08 , F02C3/145 , F04D17/105
Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.
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公开(公告)号：US20160069199A1
公开(公告)日：2016-03-10
申请号：US14783965
申请日：2014-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shelton O. Duelm , Kevin L. Rugg
CPC classification number: F01D9/042 , F01D25/246 , Y02T50/672 , Y02T50/673
Abstract: Disclosed is a gas turbine engine that includes a plurality of stator vanes. Each of the stator vanes includes an airfoil section and a platform provided at an end of the airfoil section. The platforms are provided with flanges on opposed ends thereof, and the flanges are fastened to corresponding flanges of an adjacent one of the plurality of stator vanes.
Abstract translation: 公开了一种包括多个定子叶片的燃气涡轮发动机。 每个定子叶片包括翼型部分和设置在翼型部分的端部处的平台。 平台在其相对的两端设置有凸缘，并且凸缘被紧固到多个定子叶片中相邻的一个定子叶片的对应凸缘。
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公开(公告)号：US10801351B2
公开(公告)日：2020-10-13
申请号：US15955590
申请日：2018-04-17
Applicant: United Technologies Corporation
Inventor： Kevin L. Rugg , Winston Gregory Smiddy
Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.
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Patent Agency Ranking
公开(公告)号：US10174624B1
公开(公告)日：2019-01-08
申请号：US14721393
申请日：2015-05-26
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Kevin L. Rugg , Michael G. Abbott
IPC: F01D5/28
Abstract: A blade for a gas turbine engine includes composite layers that include a uni-directional layer and a fabric compliant wedge layer that are arranged adjacent to the uni-directional layer. The fabric compliant wedge layer has a reduced compressive Young's modulus compared to the uni-directional layer.
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公开(公告)号：US10823406B2
公开(公告)日：2020-11-03
申请号：US15801557
申请日：2017-11-02
Applicant: United Technologies Corporation
Inventor： Jose E. Ruberte Sanchez , Timothy J. McAlice , Kevin L. Rugg
Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.
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公开(公告)号：US10364041B2
公开(公告)日：2019-07-30
申请号：US15218915
申请日：2016-07-25
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Arthur W. Utay , Tania Bhatia Kashyap , Thomas N. Slavens , Kevin L. Rugg , Mark F. Zelesky , Brian D. Merry , Gabriel L. Suciu
Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.
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公开(公告)号：US10358929B2
公开(公告)日：2019-07-23
申请号：US14905345
申请日：2014-07-01
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Greg C. Ojard , Kevin L. Rugg
Abstract: An airfoil includes a core with a first Young's Modulus; and an outer section at least partially surrounding the core with a second Young's Modulus, wherein the first Young's Modulus is higher than the second Young's Modulus.
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公开(公告)号：US20180156456A1
公开(公告)日：2018-06-07
申请号：US15801557
申请日：2017-11-02
Applicant: United Technologies Corporation
Inventor： Jose E. Ruberte Sanchez , Timothy J. McAlice , Kevin L. Rugg
Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.
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