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公开(公告)号：US20190331003A1
公开(公告)日：2019-10-31
申请号：US16455093
申请日：2019-06-27
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Alan W. Stoner , Edwin Otero
IPC: F01D25/28 , F01D25/24 , F01D11/12 , F01D11/00 , F01D9/04 , F01D9/02 , F01D5/28 , F01D5/24 , F01D5/22 , F16J15/16 , F01D5/26
Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
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公开(公告)号：US10378364B2
公开(公告)日：2019-08-13
申请号：US15806224
申请日：2017-11-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , David R. Pack
Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
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公开(公告)号：US20190136699A1
公开(公告)日：2019-05-09
申请号：US15806224
申请日：2017-11-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Edwin Otero , David R. Pack
CPC classification number: F01D5/187 , F01D5/186 , F01D5/188 , F02C7/18 , F04D29/324 , F04D29/542 , F05D2220/323 , F05D2240/126 , F05D2240/301 , F05D2250/11 , F05D2250/131 , F05D2260/22141
Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
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24.发明授权公开(公告)号：US09863257B2
公开(公告)日：2018-01-09
申请号：US14613724
申请日：2015-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel A Snyder , Edwin Otero , Lexia Kironn , Wendell V Twelves, Jr. , Evan Butcher
CPC classification number: F01D5/22 , B22F3/1055 , B22F5/009 , B22F7/00 , B29C64/153 , B33Y80/00 , F01D11/006 , F01D11/008 , F01D25/06 , F05D2230/22 , F05D2260/96 , Y02P10/295
Abstract: A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.
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25.发明申请公开(公告)号：US20160208621A1
公开(公告)日：2016-07-21
申请号：US14915513
申请日：2014-08-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Edwin Otero
CPC classification number: F01D5/187 , B22C9/04 , B22C9/046 , B22C9/103 , B28B1/30 , B28B7/34 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2250/232 , F05D2250/75 , F05D2260/202 , F05D2260/221 , F05D2300/20 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.
Abstract translation: 燃气涡轮发动机部件包括包括沿第一方向延伸到端壁的间隔开的第一和第二外壁的结构。 第一和第二外壁在端壁处连接以提供冷却腔。 叉骨挡板布置在冷却腔中，并且包括分别邻近第一和第二外壁的第一和第二内壁。 第一和第二内壁沿第一方向延伸并由顶点连接以提供第一腔。 叉骨挡板将第一腔与设置在顶点和端壁之间的第二腔分开。
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Patent Agency Ranking
公开(公告)号：US11306619B2
公开(公告)日：2022-04-19
申请号：US16455093
申请日：2019-06-27
Applicant: United Technologies Corporation
Inventor： Ross Wilson , Michael G. McCaffrey , John R. Farris , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Alan W. Stoner , Edwin Otero
IPC: F01D25/28 , F01D9/04 , F01D5/26 , F01D9/02 , F01D11/12 , F01D5/24 , F01D11/00 , F01D25/24 , F01D5/28 , F01D5/22 , F16J15/16
Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
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公开(公告)号：US10907482B2
公开(公告)日：2021-02-02
申请号：US16126482
申请日：2018-09-10
Applicant: United Technologies Corporation
Inventor： Daniel A. Snyder , Jaimie Schweitzer , Jonathan Perry Sandoval , Edwin Otero , Kyle C. Lana , Scott D. Virkler
Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.
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公开(公告)号：US10801348B2
公开(公告)日：2020-10-13
申请号：US14852838
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Ross Wilson , John R. Farris , Michael G. McCaffrey , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Edwin Otero , Alan W. Stoner
Abstract: Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam.
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公开(公告)号：US10370991B2
公开(公告)日：2019-08-06
申请号：US14830636
申请日：2015-08-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ross Wilson , Michael G McCaffrey , John R Farris , Theodore W Hall , John J Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , Edwin Otero , John E Paul
Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.
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30.发明申请Additive Manufactured Inseparable Platform Damper and Seal Assembly for a Gas Turbine Engine 有权用于燃气轮机发动机的添加剂制造的不可分离的平台阻尼器和密封组件公开(公告)号：US20160222798A1
公开(公告)日：2016-08-04
申请号：US14613724
申请日：2015-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel A. Snyder , Edwin Otero , Lexia Kironn , Wendell V. Twelves, JR. , Evan Butcher
CPC classification number: F01D5/22 , B22F3/1055 , B22F5/009 , B22F7/00 , B29C64/153 , B33Y80/00 , F01D11/006 , F01D11/008 , F01D25/06 , F05D2230/22 , F05D2260/96 , Y02P10/295
Abstract: A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.
Abstract translation: 用于燃气涡轮发动机的阻尼器密封组件包括相加制造的密封件和与加法制造的密封件不可分离地组装的附加制造的阻尼器。
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