-
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：US10655489B2
公开(公告)日：2020-05-19
申请号：US15862520
申请日：2018-01-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Neelesh Nandkumar Sarawate , Christopher Edward Wolfe , Victor John Morgan , Jason Ray Gregg
Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.
-
公开(公告)号：US10458254B2
公开(公告)日：2019-10-29
申请号：US15353101
申请日：2016-11-16
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Larry Steven Rosenzweig , Changjie Sun , Ananda Barua
Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.
-
公开(公告)号：US10385865B2
公开(公告)日：2019-08-20
申请号：US15063089
申请日：2016-03-07
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Changjie Sun , Ananda Barua
Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.
-
公开(公告)号：US20180258789A1
公开(公告)日：2018-09-13
申请号：US15452473
申请日：2017-03-07
Applicant: General Electric Company
Inventor： Rahul Anil Bidkar , Neelesh Nandkumar Sarawate , Kevin McMahan , Ronald Chila
CPC classification number: F01D25/12 , F01D9/023 , F01D11/003 , F01D11/005 , F01D25/08 , F01D25/243 , F01D25/28 , F01D25/30 , F04D29/545 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2260/201 , F23R3/002 , F23R3/005 , F23R3/60 , F23R2900/00012
Abstract: A system includes a web plate axially disposed between a transition piece and a turbine nozzle. The web plate includes a radial arm extending in a radial direction between an inner surface and an outer surface of the web plate. The radial arm, the inner surface, and the outer surface are disposed about an axial passage configured to facilitate a flow of combustion products from the transition piece to the turbine nozzle. The transition piece is disposed within a compressor discharge cavity configured to receive an oxidant. The radial arm includes an upstream face in fluid communication with the compressor discharge cavity. The radial arm also includes an arm passage that extends an axial length in an axial direction from the upstream face through at least an axial depth of the radial arm. The arm passage is configured to receive a portion of the oxidant through the upstream face.
-
Patent Agency Ranking
公开(公告)号：US20180216479A1
公开(公告)日：2018-08-02
申请号：US15418707
申请日：2017-01-28
Applicant: General Electric Company
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate
CPC classification number: F01D11/005 , F01D9/047 , F01D11/003 , F05D2220/32 , F05D2230/30 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F16J15/02
Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots having a seal assembly disposed therein. The seal assembly including an intersegment seal including a plurality of seal segments defining one or more end regions. One or more of the plurality of seal segments including at the one or more end regions a plurality of jet holes and a channel having a wire disposed therein, wherein the intersegment seal provides sealing of one or more end gaps defined proximate the one or more end regions in response to the thrust of a flow of pressurized air through the plurality of jet holes.
-
公开(公告)号：US20180135646A1
公开(公告)日：2018-05-17
申请号：US15353101
申请日：2016-11-16
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Larry Steven Rosenzweig , Changjie Sun , Ananda Barua
IPC: F04D29/38
Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.
-
公开(公告)号：US20170254340A1
公开(公告)日：2017-09-07
申请号：US15063089
申请日：2016-03-07
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Changjie Sun , Ananda Barua
IPC: F04D29/32
CPC classification number: F04D29/324 , F04D29/164
Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.
-
公开(公告)号：US20160024951A1
公开(公告)日：2016-01-28
申请号：US14337453
申请日：2014-07-22
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
CPC classification number: F01D11/005 , F05D2240/59 , F16J15/02 , F16J15/0812
Abstract: The present application provides seal assemblies having improved flexibility for reducing leakages between adjacent misaligned components of turbomachinery. The seal assemblies include a first outer shim formed of a flexible permeable material and a second outer shim formed of a substantially impervious material. At least the second outer shim is configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the first and second outer shims. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to meet operating requirements associated with turbomachinery. A turbomachine including the seal assembly is provided.
Abstract translation: 本申请提供了具有改进的柔性的密封组件，用于减少涡轮机械的相邻不对准部件之间的泄漏。 密封组件包括由柔性可渗透材料形成的第一外垫片和由基本上不可渗透的材料形成的第二外垫片。 至少第二外垫片构造成用于与相邻部件的密封槽密封接合。 密封组件还可以包括位于第一和第二外垫片之间的内垫片和填料层中的至少一个。 密封组件可以足够灵活以考虑相邻部件之间的不对准，足够坚硬以满足组装要求，并且足够坚固以满足与涡轮机械相关的操作要求。 提供包括密封组件的涡轮机。
-
公开(公告)号：US20140062032A1
公开(公告)日：2014-03-06
申请号：US13690541
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Christopher Edward Wolfe , Victor John Morgan , Neelesh Nandkumar Sarawate , David Wayne Weber
IPC: F01D11/00
CPC classification number: F01D11/005 , F05D2240/57 , F16J15/128
Abstract: A seal assembly is provided. The seal assembly includes a first outer shim and a second outer shim The second outer shim is operably coupled to the first outer shim and comprises at least one substantially impermeable portion that spans across a gap between at least two turbomachine components. The second outer shim further engages the at least two turbomachine components to substantially seal the gap. The substantially impermeable portion is substantially planar at least along a width of the seal assembly. The seal assembly further includes a resilient member that is either coupled to at least a portion of an outer surface of the first outer shim or comprises an integral portion of the first outer shim The resilient member engages the seal assembly to contact bottom surfaces of a cavity defined between the at least two turbomachine components.
Abstract translation: 提供密封组件。 密封组件包括第一外垫片和第二外垫片第二外垫片可操作地联接到第一外垫片，并且包括穿过至少两个涡轮机构件之间的间隙的至少一个基本不可渗透部分。 第二外垫片进一步接合至少两个涡轮机组件以基本上密封间隙。 至少沿着密封组件的宽度，基本上不可渗透部分基本上是平面的。 密封组件还包括弹性构件，其被联接到第一外垫片的外表面的至少一部分，或包括第一外垫片的整体部分。弹性构件接合密封组件以接触空腔的底表面 限定在所述至少两个涡轮机组件之间。
-
-
-
-
-
-
-
-
-
Search Results
68
records
(took 0.019 seconds)
