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公开(公告)号：US11268394B2
公开(公告)日：2022-03-08
申请号：US16817742
申请日：2020-03-13
Applicant: General Electric Company
Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.
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公开(公告)号：US20190242263A1
公开(公告)日：2019-08-08
申请号：US16386578
申请日：2019-04-17
Applicant: General Electric Company
Inventor： David Alan Frey , Samir Armando Salamah , Charles William Craig, III
CPC classification number: F01D9/041 , F01D5/187 , F05D2230/50 , F05D2260/20 , F05D2260/208 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: Ceramic matrix composite (CMC) airfoils and methods for forming CMC airfoils are provided. In one embodiment, an airfoil is provided that includes opposite pressure and suction sides extending radially along a span and opposite leading and trailing edges extending radially along the span. The leading edge defines a forward end of the airfoil, and the trailing edge defines an aft end of the airfoil. A trailing edge portion is defined adjacent the trailing edge at the aft end, and a pocket is defined in and extends within the trailing edge portion. A heat pipe is received in the pocket. A method for forming an airfoil is provided that includes laying up a CMC material to form an airfoil preform assembly; processing the airfoil preform assembly; defining a pocket in a trailing edge portion of the airfoil; and inserting a heat pipe into the pocket.
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公开(公告)号：US20170328228A1
公开(公告)日：2017-11-16
申请号：US15155115
申请日：2016-05-16
Applicant: General Electric Company
Inventor： Michael Anthony Ruthemeyer , David Alan Frey
CPC classification number: F01D11/005 , F01D5/225 , F01D9/00 , F01D9/04 , F01D11/00 , F02C3/04 , F05D2220/32 , F05D2240/11 , F05D2240/55 , Y02T50/672
Abstract: The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap therebetween, and the first and the third shroud segments define a gap therebetween. A first seal portion is positioned at least partially on the first and the third shroud segments and at least partially covers the gap defined by the first and the third shroud segments. A second seal portion is positioned at least partially on the first and the second shroud segments and at least partially covers the gap defined by the first and the second shroud segments. A third seal portion extends between and couples the first and the second seal portions.
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公开(公告)号：US20170268359A1
公开(公告)日：2017-09-21
申请号：US15075363
申请日：2016-03-21
Applicant: General Electric Company
Inventor： David Alan Frey
IPC: F01D11/00
CPC classification number: F01D25/246 , F01D11/02 , F05D2240/11 , F05D2300/6033 , Y02T50/672
Abstract: An ingestion restricting device is provided, which is particularly useful in a turbine engine. The ingestion restricting device can include a first component defining a first edge and including a plurality of ceramic matrix composite (CMC) plies forming outer, inner, and intermediate layers. The ingestion restricting device can also include a second component adjacent to the first component and defining a second edge. The first edge of the first component is opposite the second edge of the second component and defines a gap therebetween. Also, at least one ply of the plurality of CMC plies in the outer layer of the first component comprises an integral protrusion extending from the first edge a distance sufficient to traverse the gap and to overlap the second edge of the second component.
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公开(公告)号：US11846207B2
公开(公告)日：2023-12-19
申请号：US17685523
申请日：2022-03-03
Applicant: General Electric Company
CPC classification number: F01D9/042 , F01D5/18 , F01D25/246 , F02C7/28 , F01D5/282 , F01D5/284 , F05D2230/60 , F05D2300/6033
Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.
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Patent Agency Ranking
公开(公告)号：US11193392B2
公开(公告)日：2021-12-07
申请号：US15075363
申请日：2016-03-21
Applicant: General Electric Company
Inventor： David Alan Frey
Abstract: An ingestion restricting device is provided, which is particularly useful in a turbine engine. The ingestion restricting device can include a first component defining a first edge and including a plurality of ceramic matrix composite (CMC) plies forming outer, inner, and intermediate layers. The ingestion restricting device can also include a second component adjacent to the first component and defining a second edge. The first edge of the first component is opposite the second edge of the second component and defines a gap therebetween. Also, at least one ply of the plurality of CMC plies in the outer layer of the first component comprises an integral protrusion extending from the first edge a distance sufficient to traverse the gap and to overlap the second edge of the second component.
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公开(公告)号：US20210017869A1
公开(公告)日：2021-01-21
申请号：US16513226
申请日：2019-07-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , David Alan Frey , Kirk D. Gallier , Steven Robert Brassfield
Abstract: A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.
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公开(公告)号：US20200024966A1
公开(公告)日：2020-01-23
申请号：US16039812
申请日：2018-07-19
Applicant: General Electric Company
Inventor： Charles William Craig, III , David Alan Frey
Abstract: Airfoils, additively manufactured airfoils, and methods of manufacturing airfoils are provided. For example, an airfoil comprises opposite pressure and suction sides that extend axially from a leading edge to a trailing edge and radially spaced apart inner and outer ends. The airfoil also comprises an outer wall defining the pressure and suction sides and leading and trailing edges. A rib extends within the airfoil from the pressure side to the suction side of the outer wall and radially from the inner to the outer end. The airfoil further comprises a first pre-impingement chamber surrounded by a first post-impingement chamber and a first dividing wall segment separating the first pre-impingement and first post-impingement chambers and having a plurality of cooling holes defined therein. The outer wall, rib, and first dividing wall segment are integrally formed as a single monolithic component.
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公开(公告)号：US20200024965A1
公开(公告)日：2020-01-23
申请号：US16039646
申请日：2018-07-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Alan Frey , Kirk D. Gallier
Abstract: An apparatus and method relating an airfoil for a turbine engine with an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The airfoil includes a first cooling passage extending in the span-wise direction within the interior and a second cooling passage defining an impingement surface and located proximate the first cooling passage, an interior wall separating the first cooling passage from the second cooling passage, and at least one cooling hole passing through the interior wall.
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公开(公告)号：US20180045063A1
公开(公告)日：2018-02-15
申请号：US15232880
申请日：2016-08-10
Applicant: General Electric Company
Inventor： David Alan Frey , Samir Armando Salamah , Charles William Craig, III
CPC classification number: F01D9/041 , F01D5/187 , F05D2230/50 , F05D2260/20 , F05D2260/208 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: Ceramic matrix composite (CMC) airfoils and methods for forming CMC airfoils are provided. In one embodiment, an airfoil is provided that includes opposite pressure and suction sides extending radially along a span and opposite leading and trailing edges extending radially along the span. The leading edge defines a forward end of the airfoil, and the trailing edge defines an aft end of the airfoil. A trailing edge portion is defined adjacent the trailing edge at the aft end, and a pocket is defined in and extends within the trailing edge portion. A heat pipe is received in the pocket. A method for forming an airfoil is provided that includes laying up a CMC material to form an airfoil preform assembly; processing the airfoil preform assembly; defining a pocket in a trailing edge portion of the airfoil; and inserting a heat pipe into the pocket.
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