-
公开(公告)号：US20140334929A1
公开(公告)日：2014-11-13
申请号：US13892414
申请日：2013-05-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner
CPC classification number: F04D29/5853 , F04D29/322
Abstract: A heat shield for a rotor in a turbine engine is provided. The heat shield includes a main body having a first pair of recesses. The first pair of recesses is adapted to fit around a portion of one or more rotor blades or between two axially adjacent rotor wheels. The first pair of recesses limits axial and radial movement of the heat shield by interaction with the rotor blades or by interaction with the two axially adjacent rotor wheels. The first pair of recesses engage axially adjacent rotor blades or the axially adjacent rotor wheels. The heat shield protects the rotor from hot gas.
Abstract translation: 提供了一种用于涡轮发动机中的转子的隔热罩。 隔热罩包括具有第一对凹部的主体。 第一对凹槽适于围绕一个或多个转子叶片的一部分或两个轴向相邻的转子轮之间。 第一对凹槽通过与转子叶片的相互作用或通过与两个轴向相邻的转子轮的相互作用来限制隔热罩的轴向和径向移动。 第一对凹槽与轴向相邻的转子叶片或轴向相邻的转子轮啮合。 热屏蔽保护转子免受热气。
-
公开(公告)号：US11767766B1
公开(公告)日：2023-09-26
申请号：US17877085
申请日：2022-07-29
Applicant: General Electric Company
Inventor： John M. Matthews , Christopher Donald Porter , Matthew Troy Hafner
CPC classification number: F01D5/187 , F01D9/06 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2260/201
Abstract: An airfoil includes a leading edge, a trailing edge, a base, and a tip. The airfoil further includes a pressure side wall and a suction side wall that extend between the leading edge, the trailing edge, the base, and the tip. The airfoil further includes a plurality of passages that are defined within the airfoil and extend from an inlet at one of the base or the tip. Each passage of the plurality of passages is defined at least partially by a primary impingement wall and a solid side wall. The primary impingement wall is spaced apart from one of the pressure side wall or the suction side wall such that a primary impingement gap is defined therebetween. The primary impingement wall defines a plurality of impingement apertures that direct air in discrete jets across the impingement gap to impinge upon an interior surface of the airfoil.
-
公开(公告)号：US11097384B2
公开(公告)日：2021-08-24
申请号：US16254855
申请日：2019-01-23
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John Ellington Greene
Abstract: Various embodiments include a metal-repaired ceramic matrix composite (CMC) article, and a method of repairing a CMC article having a defect. Particular embodiments include a method including: removing a defect-containing portion of the CMC article; forming at least one opening in a remaining portion of the CMC article; preparing a metal repair preform for replacing at least the removed portion of the CMC article, wherein a portion of the metal repair preform complements the at least one opening; and attaching the metal repair preform to the remaining portion of the CMC article.
-
公开(公告)号：US10731494B2
公开(公告)日：2020-08-04
申请号：US15298572
申请日：2016-10-20
Applicant: General Electric Company
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Matthew Troy Hafner
Abstract: Various embodiments include gas turbine seals and methods of forming such seals for advanced gas path (AGP) heat transfer designed gas turbine engines. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component formed of a ceramic matrix composite and including a seal slot located in an end face, each seal slot having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and an overhanging seal assembly disposed in the seal slot. The overhanging seal assembly including an intersegment seal including a plurality of seal segments defining two vertical seal segments and a plurality of horizontal seal segments and a first overhanging positioner shim seal and a second overhanging positioner shim seal, each including an extended portion. The overhanging seal assembly disposed in the seal slot so as to provide position constrainment of the two vertical seal segments.
-
公开(公告)号：US10731471B2
公开(公告)日：2020-08-04
申请号：US16235095
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , John McConnell Delvaux , Matthew Troy Hafner , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.
-
Patent Agency Ranking
公开(公告)号：US20200224540A1
公开(公告)日：2020-07-16
申请号：US16247327
申请日：2019-01-14
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Matthew Troy Hafner , Russell Pierson DeForest
Abstract: An insert system for an airfoil plenum includes a first insert and a second insert that include a plurality of impingement openings defined therein. The first insert includes a forward-facing inlet opening. The second insert includes a neck portion having a radial-facing inlet opening, an aft opening, and a cavity in flow communication between the radial-facing inlet opening and the aft opening. The second insert is sized for insertion into the plenum radially through a plenum inlet such that the neck portion is positioned in the plenum inlet. The first insert is sized for insertion into the second insert radially through the radial-facing inlet opening. When the neck portion is positioned in the plenum inlet, the first insert is moveable aftward through the aft opening into an installed position such that the forward-facing inlet opening opens into the cavity.
-
公开(公告)号：US10590776B2
公开(公告)日：2020-03-17
申请号：US15174332
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
-
公开(公告)号：US10287894B2
公开(公告)日：2019-05-14
申请号：US15174182
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
IPC: F01D5/18 , B33Y10/00 , B33Y80/00 , B23K26/342 , B23K26/70 , B22F3/105 , B22F3/24 , B23K15/00 , B23K26/00 , C23C28/04 , F01D9/02 , F01D25/12 , F01D5/14 , F01D5/28 , B23K101/00 , B23K103/08
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
-
公开(公告)号：US09441639B2
公开(公告)日：2016-09-13
申请号：US13892414
申请日：2013-05-13
Applicant: General Electric Company
Inventor： Matthew Troy Hafner
CPC classification number: F04D29/5853 , F04D29/322
Abstract: A heat shield for a rotor in a turbine engine is provided. The heat shield includes a main body having a first pair of recesses. The first pair of recesses is adapted to fit around a portion of one or more rotor blades or between two axially adjacent rotor wheels. The first pair of recesses limits axial and radial movement of the heat shield by interaction with the rotor blades or by interaction with the two axially adjacent rotor wheels. The first pair of recesses engage axially adjacent rotor blades or the axially adjacent rotor wheels. The heat shield protects the rotor from hot gas.
Abstract translation: 提供了一种用于涡轮发动机中的转子的隔热罩。 隔热罩包括具有第一对凹部的主体。 第一对凹槽适于围绕一个或多个转子叶片的一部分或两个轴向相邻的转子轮之间。 第一对凹槽通过与转子叶片的相互作用或通过与两个轴向相邻的转子轮的相互作用来限制隔热罩的轴向和径向移动。 第一对凹槽与轴向相邻的转子叶片或轴向相邻的转子轮啮合。 热屏蔽保护转子免受热气。
-
公开(公告)号：US20150010384A1
公开(公告)日：2015-01-08
申请号：US13937121
申请日：2013-07-08
Applicant: General Electric Company
Inventor： Matthew Troy Hafner
IPC: F01D11/00
CPC classification number: F01D11/008 , F01D5/3015 , F05D2230/60 , F05D2240/55 , Y10T29/49245
Abstract: A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage with a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage with a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal assembly extending axially between the first and second turbine stages. The interstage seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first seal. The interstage seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate includes a second seal. The interstage seal assembly also includes a spacer wheel extending from a rotor shaft and configured to engage with the first coverplate and the second coverplate.
Abstract translation: 系统包括多级涡轮机。 所述多级涡轮机包括具有第一轮的第一涡轮级，所述第一轮具有围绕所述第一车轮周向间隔开的多个第一叶片段，具有第二轮的第二涡轮级，所述第二轮具有围绕所述第二轮围绕圆周间隔开的多个第二叶片段， 以及在第一和第二涡轮级之间轴向延伸的级间密封组件。 级间密封组件包括联接到第一涡轮级的第一盖板。 第一盖板包括第一密封件。 级间密封组件还包括联接到第二涡轮级的第二盖板。 第二盖板包括第二密封件。 级间密封组件还包括从转子轴延伸并且构造成与第一盖板和第二盖板接合的隔离轮。
-
-
-
-
-
-
-
-
-
Search Results
78
records
(took 0.019 seconds)
