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公开(公告)号：US10415579B2
公开(公告)日：2019-09-17
申请号：US15278860
申请日：2016-09-28
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Larry Steven Rosenzweig , Sathyanarayanan Raghavan , Changjie Sun , Ananda Barua , Jinjie Shi
Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.
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公开(公告)号：US09995160B2
公开(公告)日：2018-06-12
申请号：US14578816
申请日：2014-12-22
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Kirk D. Gallier , Robert Frederick , Darrell Senile , Benjamin Huizenga
CPC classification number: F01D9/065 , F01D5/282 , F01D5/284 , F01D11/005 , F01D25/162 , F05D2300/6033 , Y02T50/672
Abstract: An airfoil profile-shaped seal is disposable between an inside surface of a hollow airfoil body and a seal support. The seal includes an elongated member defining a generally closed curve having a generally straight portion, a generally curved portion, and having a solid cross-section across and along the length of the elongated member. When the seal is disposed in an airfoil profile-shaped groove of a seal support adjacent to the inner surface of the hollow airfoil body, and a fluid pressure on one side of the seal is greater than a fluid pressure on the other side of the seal, portions of the seal engage the inner surface of the hollow airfoil body and a surface of the groove to form a seal to inhibit leakage of fluid from the one side to the other side.
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公开(公告)号：US20180135638A1
公开(公告)日：2018-05-17
申请号：US15353182
申请日：2016-11-16
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Luc Stephane Leblanc , Sathyanarayanan Raghavan , Changjie Sun , Ananda Barua
CPC classification number: F04D29/023 , F04D29/526 , F05D2300/20
Abstract: Coating systems for components of a gas turbine engine, such as a compressor casing, are provided. The coating system can include a ceramic material disposed along the compressor casing on a surface to be adjacent to a rotating compressor blade. The coating system is harder than the compressor blade and can reduce the rub ratio between the casing and blade. The coating system can thereby increase the lifetime of the compressor casing and blades. Methods are also provided for applying the coating system onto a compressor casing.
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Patent Agency Ranking
公开(公告)号：US20170370239A1
公开(公告)日：2017-12-28
申请号：US15189122
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Venkat Subramaniam Venkataramani , Neelesh Nandkumar Sarawate , Anthony Christopher Marin , Wayne Charles Hasz , Stephen Francis Bancheri , Edip Sevincer
CPC classification number: F01D11/005 , F01D11/08 , F01D25/005 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F05D2250/62 , F05D2300/21 , F05D2300/2112 , F05D2300/2118 , F05D2300/2283 , F05D2300/5021 , F05D2300/5023 , F05D2300/518 , F05D2300/6033 , F05D2300/609 , F16J15/102
Abstract: A turbine system including a sealing component is presented. The sealing component includes a ceramic material. The ceramic material includes grains having an average grain size of less than 10 microns. A turbine shroud assembly including the sealing component is also presented.
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公开(公告)号：US09759081B2
公开(公告)日：2017-09-12
申请号：US14049020
申请日：2013-10-08
Applicant: General Electric Company
Inventor： Victor John Morgan , Gregory Thomas Foster , Neelesh Nandkumar Sarawate , David Wayne Weber
CPC classification number: F01D11/08 , F01D9/041 , F01D11/003 , F05D2230/60 , F05D2260/38 , Y10T29/4932
Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
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公开(公告)号：US20170159479A1
公开(公告)日：2017-06-08
申请号：US14963019
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert
CPC classification number: F01D11/006 , F01D25/246 , F04D29/083 , F05D2240/57 , F05D2250/61
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 an upstream corner shim and a downstream corner shim, where one of the upstream corner shim or the downstream corner shim includes a pressure actuation feature configured to block a flow of gas between the two components.
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67.发明申请System and Method Including a Circumferential Seal Assembly to Facilitate Sealing in a Turbine 审中-公开包括周向密封组件以便于在涡轮机中密封的系统和方法公开(公告)号：US20160177762A1
公开(公告)日：2016-06-23
申请号：US14577549
申请日：2014-12-19
Applicant: General Electric Company
CPC classification number: F01D11/005 , F01D11/001 , F01D11/02 , F02C3/04 , F05D2240/55
Abstract: A method and system including a circumferential seal assembly for sealing between components within a turbine is provided. A circumferential seal assembly is disposed in a slot extending circumferentially about an inner barrel. The seal assembly includes a first shim layer and at least one additional shim layer configured in an overlapping stacked configuration so as to stagger the end portions of each of the shim segments defined by the shim layers, relative to one another and circumferentially about the seal assembly. One or more cloth layers are configured wrapping about the first shim layer and the at least one additional shim layer to define a sealing member having a first sealing surface and a second sealing surface. The assembly further including a base plate, wherein the sealing member is disposed on an upper surface of the base plate to provide for sealing engagement between the components of the turbine.
Abstract translation: 提供了一种方法和系统，其包括用于在涡轮机内的部件之间进行密封的周向密封组件。 周向密封组件设置在围绕内筒周向延伸的狭槽中。 密封组件包括第一垫片层和至少一个以重叠堆叠构造构造的附加垫片，以便使由垫片层限定的每个垫片段的端部相对于彼此并且围绕密封组件周向地错开 。 配置一个或多个布层围绕第一垫片层和至少一个附加垫片层缠绕以限定具有第一密封表面和第二密封表面的密封构件。 组件还包括基板，其中密封构件设置在基板的上表面上，以提供涡轮机部件之间的密封接合。
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公开(公告)号：US20140154062A1
公开(公告)日：2014-06-05
申请号：US13690485
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Wayne Weber , Kevin Richard Kirtley , Victor John Morgan , Neelesh Nandkumar Sarawate
IPC: F02C7/28
CPC classification number: F02C7/28 , F01D11/00 , F01D11/005 , F01D11/006 , F05D2230/90 , F05D2240/55 , F05D2240/57 , F05D2300/43 , F05D2300/611 , Y10T29/49229
Abstract: A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed.
Abstract translation: 用于放置在燃气涡轮机的两个涡轮机部件之间以密封部件之间的间隙的狭槽中的密封件可以包括密封元件，其尺寸设计成能够放置在槽内并且在燃气轮机的操作期间基本上密封间隙 。 牺牲涂层可以位于密封元件上。 牺牲涂层可以被配置成基本上符合狭缝尺寸的尺寸，牺牲涂层包括可通过加热将其从密封元件移除到燃气涡轮机运行期间达到的温度的材料。 还公开了相关的燃气轮机组件和组装方法。
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