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11.发明授权公开(公告)号：US10738644B2
公开(公告)日：2020-08-11
申请号：US15690307
申请日：2017-08-30
Applicant: General Electric Company
Inventor： Jinjie Shi , Dennis Paul Dry , Christopher Edward Wolfe , Andres Jose Garcia-Crespo , Yun Zhu
Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.
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公开(公告)号：US20200166142A1
公开(公告)日：2020-05-28
申请号：US16201564
申请日：2018-11-27
Applicant: General Electric Company
Inventor： Rahul Anil Bidkar , Christopher Edward Wolfe , Nathan Evan McCurdy Gibson , Rodrigo Rodriguez Erdmenger , Deepak Trivedi , Quang Tue Nguyen Tran
Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.
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公开(公告)号：US10563772B2
公开(公告)日：2020-02-18
申请号：US15810183
申请日：2017-11-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Deepak Trivedi , Christopher Edward Wolfe , Nathan EvanMcCurdy Gibson , Brian Joseph Prenger
Abstract: A seal assembly, for example, a face seal assembly for a machine such as a turbomachine, and an associated method of operating the seal assembly in the machine are disclosed. The seal assembly includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, an end of the first flexure and an end of the second flexure are coupled to each other and to the non-rotatable seal component.
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公开(公告)号：US20180306120A1
公开(公告)日：2018-10-25
申请号：US15493549
申请日：2017-04-21
Applicant: General Electric Company
Inventor： Jinjie Shi , Stephen Gerard Schadewald , Jason Paul Hoppa , Kirk Douglas Gallier , Christopher Edward Wolfe , Robert Proctor
CPC classification number: F02C7/28 , F01D9/02 , F02C3/04 , F02C9/18 , F05D2220/32 , F05D2240/58 , F16J15/164 , F16J15/34 , F23R3/002
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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公开(公告)号：US20180187673A1
公开(公告)日：2018-07-05
申请号：US15397514
申请日：2017-01-03
Applicant: General Electric Company
Inventor： Deepak Trivedi , Christopher Edward Wolfe , Brian Paul Reeves , Bodhayan Dev
CPC classification number: F04B47/08 , E21B43/121 , E21B43/128 , F04B2203/0903 , F15B1/02 , F15B11/10 , F15B15/1428 , F15B15/1447 , F15B15/22 , F15B2211/205 , F15B2211/212 , F15B2211/755
Abstract: An actuator for use with a fluid transfer device is provided. The actuator includes a piston cylinder having a longitudinal axis and defining a piston chamber having both a head end and a longitudinally opposite base end. The actuator further includes a piston disposed within the piston chamber. The piston movable between a first piston position proximate the piston chamber head end and a second piston position proximate the piston chamber base end. The piston includes a piston head end having a first indexing mechanism, a first piston seal, and at least one first feed hole. The piston further includes a base end longitudinally opposite the head end having a second indexing mechanism, a guide tooth, a second piston seal, and at least one second feed hole. The piston defines a plurality of channels that extends from proximate the first piston seal to proximate the second piston seal.
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Patent Agency Ranking
公开(公告)号：US20180087387A1
公开(公告)日：2018-03-29
申请号：US15278821
申请日：2016-09-28
Applicant: General Electric Company
Inventor： Jinjie Shi , Larry Steven Rosenzweig , Christopher Edward Wolfe , Dennis Paul Dry
CPC classification number: F01D5/288 , F01D11/122 , F05D2230/90 , F05D2240/307 , F05D2300/175 , F05D2300/506 , F05D2300/6012 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/6765
Abstract: Coating systems for a turbine blade tip, such as a metal turbine blade tip, are provided. The coating system can include a thermal barrier coating on the surface of the turbine blade tip as well as one or more bond coats and/or metallic coatings. The coated blade tip can be used with a ceramic matrix composite shroud coated with an environmental barrier coating to reduce blade tip wear. Methods are also provided for applying the coating system onto a turbine blade tip.
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公开(公告)号：US20170159480A1
公开(公告)日：2017-06-08
申请号：US14963034
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert , Christopher Edward Wolfe
CPC classification number: F01D11/006 , F01D5/02 , F01D9/02 , F01D11/003 , F01D11/005 , F05D2220/32 , F05D2230/23 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2300/177 , F05D2300/20 , F16J15/08
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include a first intersegment seal, a second intersegment seal, and a rope seal that are configured to block a flow of gas between the two components.
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18.发明申请公开(公告)号：US20150204182A1
公开(公告)日：2015-07-23
申请号：US14157803
申请日：2014-01-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Emad Andarawis Andarawis , Daniel White Sexton , Christopher Edward Wolfe , Edward James Nieters , Yuri Alexeyevich Plotnikov , Michael Joseph Dell'Anno
IPC: E21B47/00
CPC classification number: E21B47/0001 , E21B33/06 , E21B47/09
Abstract: A system to detect a position of a pipe with respect to a BOP includes a casing disposed around an outer surface of a section of the pipe. The system further includes sensing devices that are disposed on the casing and arranged to form a plurality of arrays and configured to generate position signals. The arrays are disposed circumferentially around the casing and spaced from one another along the length of the casing. The system includes a processing unit configured to compute distance between the pipe and each sensing device. The processing unit generates a first alert when the distance between the pipe and at least one sensing device is different from a reference distance. The processing unit generates a second alert when the distance between the pipe and each sensing device of at least one array of sensing devices is different from the reference distance.
Abstract translation: 用于检测管道相对于BOP的位置的系统包括围绕管的一部分的外表面设置的壳体。 该系统还包括设置在壳体上并被布置成形成多个阵列并被配置为产生位置信号的感测装置。 阵列围绕壳体周向设置并且沿着壳体的长度彼此间隔开。 该系统包括被配置为计算管道和每个感测装置之间的距离的处理单元。 当管和至少一个感测装置之间的距离与参考距离不同时，处理单元产生第一警报。 当至少一个感测装置阵列的管道和每个感测装置之间的距离与参考距离不同时，处理单元产生第二警报。
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公开(公告)号：US20220128236A1
公开(公告)日：2022-04-28
申请号：US17647235
申请日：2022-01-06
Applicant: General Electric Company
Inventor： Jinjie Shi , Robert Proctor , Jason Paul Hoppa , Stephen Gerard Schadewald , Christopher Edward Wolfe , Kirk Douglas Gallier
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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公开(公告)号：US10900570B2
公开(公告)日：2021-01-26
申请号：US16201564
申请日：2018-11-27
Applicant: General Electric Company
Inventor： Rahul Anil Bidkar , Christopher Edward Wolfe , Nathan Evan McCurdy Gibson , Rodrigo Rodriguez Erdmenger , Deepak Trivedi , Quang Tue Nguyen Tran
Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.
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