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公开(公告)号：US10316686B2
公开(公告)日：2019-06-11
申请号：US15359066
申请日：2016-11-22
Applicant: United Technologies Corporation
Inventor： Eric A. Hudson , Stephen K. Kramer
Abstract: An actuation system according to various embodiments can include an actuation ring having a first end and a second end separated by a gap, the actuation ring being configured to be coupled to a blade outer air seal (BOAS). The actuation system can also include an actuator coupled to at least one of the first end or the second end and configured to adjust a size of the gap such that a tip clearance between the BOAS and a blade tip is reduced in response to the size of the gap being reduced.
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公开(公告)号：US20180135441A1
公开(公告)日：2018-05-17
申请号：US15354118
申请日：2016-11-17
Applicant: United Technologies Corporation
Inventor： Eric A. Hudson
CPC classification number: F01D9/02 , F01D5/14 , F01D5/288 , F02C3/04 , F04D29/023 , F04D29/324 , F04D29/542 , F05D2220/32 , F05D2230/90 , F05D2240/124 , F05D2240/306 , F05D2240/35 , F05D2250/20 , F05D2250/28 , F05D2300/17 , F05D2300/20 , F05D2300/608
Abstract: An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.
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公开(公告)号：US20160208645A1
公开(公告)日：2016-07-21
申请号：US15049775
申请日：2016-02-22
Applicant: United Technologies Corporation
Inventor： Susan M. Tholen , Dominic J. Mongillo , Paul M. Lutjen , James N. Knapp , Virginia L. Ross , Jonathan J. Earl , Eric A. Hudson
Abstract: A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal.
Abstract translation: 用于叶片外部空气密封件的冷却方案包括构造成对流地冷却叶片外部空气密封件的周边的周边冷却装置，以及配置成通过冲击冷却来冷却叶片外部空气密封件的中心部分的芯部冷却装置，并提供 膜冷却到叶片外部空气密封件的内径面。
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公开(公告)号：US10465545B2
公开(公告)日：2019-11-05
申请号：US15980855
申请日：2018-05-16
Applicant: United Technologies Corporation
Inventor： Alan D. Cetel , Dilip M. Shah , Eric A. Hudson , Raymond Surace
Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.
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公开(公告)号：US20190091759A1
公开(公告)日：2019-03-28
申请号：US16106294
申请日：2018-08-21
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , James T. Auxier , Eric A. Hudson
Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.
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Patent Agency Ranking
公开(公告)号：US10184353B2
公开(公告)日：2019-01-22
申请号：US15049775
申请日：2016-02-22
Applicant: United Technologies Corporation
Inventor： Susan M. Tholen , Dominic J. Mongillo , Paul M. Lutjen , James N. Knapp , Virginia L. Ross , Jonathan J. Earl , Eric A. Hudson
Abstract: A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal.
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公开(公告)号：US20180202306A1
公开(公告)日：2018-07-19
申请号：US15405778
申请日：2017-01-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Eric A. Hudson , Michael G. McCaffrey , Stanley J. Funk , Scott D. Virkler
IPC: F01D11/18 , F01D5/20 , F01D25/24 , F01D11/02 , F02C3/04 , F04D29/32 , F04D29/52 , F04D29/08 , F04D29/64
CPC classification number: F01D11/18 , F01D5/20 , F01D11/025 , F01D25/246 , F02C3/04 , F04D29/083 , F04D29/324 , F04D29/526 , F04D29/642 , F05D2220/32 , F05D2240/11 , F05D2240/307 , F05D2240/55 , F05D2300/171 , F05D2300/177
Abstract: A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.
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公开(公告)号：US10012099B2
公开(公告)日：2018-07-03
申请号：US15004591
申请日：2016-01-22
Applicant: United Technologies Corporation
Inventor： Alan D. Cetel , Dilip M. Shah , Eric A. Hudson , Raymond Surace
CPC classification number: F01D11/005 , C22C19/00 , F01D25/005 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/26 , F05D2230/90
Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.
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公开(公告)号：US09803559B2
公开(公告)日：2017-10-31
申请号：US14615665
申请日：2015-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew D. Burdick , Thomas J. Praisner , Andrew S. Aggarwala , Eric A. Hudson , Michael G. McCaffrey
CPC classification number: F02C9/20 , F01D5/148 , F01D9/02 , F01D11/025 , F01D17/162 , F02C3/04 , F05D2240/122 , Y02T50/672 , Y02T50/673 , Y10T137/0536
Abstract: One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion.
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公开(公告)号：US20170211401A1
公开(公告)日：2017-07-27
申请号：US15004591
申请日：2016-01-22
Applicant: United Technologies Corporation
Inventor： Alan D. Cetel , Dilip M. Shah , Eric A. Hudson , Raymond Surace
CPC classification number: F01D11/005 , C22C19/00 , F01D25/005 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/26 , F05D2230/90
Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.
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