公开(公告)号：US20180291749A1

公开(公告)日：2018-10-11

申请号：US15481674

申请日：2017-04-07

Applicant: General Electric Company

Inventor： Neelesh Nandkumar SARAWATE

IPC: F01D5/22 ,  F01D5/14 ,  F01D11/00 ,  F01D11/22

CPC classification number: F01D5/225 ,  F01D5/34 ,  F01D11/006 ,  F01D11/008 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/672 ,  Y02T50/676

Abstract: A shroud assembly of a turbine system is presented. The shroud assembly includes a plurality of outer shroud segments disposed annularly and defining a first gap between a pair of outer shroud segments of the plurality of outer shroud segments; a plurality of inner shroud segments disposed annularly and radially inward of the plurality of outer shroud segments, and defining a second gap between a pair of inner shroud segments of the plurality of inner shroud segments, wherein the plurality of inner shroud segments is same in number to the plurality of outer shroud segments, and wherein the first gap and the second gap are offset; and an impingement plate coupled to an outer shroud segment of the pair of outer shroud segments and interposed between the outer shroud segment and the pair of inner shroud segments.

公开(公告)号：US20200165713A1

公开(公告)日：2020-05-28

申请号：US16632648

申请日：2017-07-18

Applicant: General Electric Company

Inventor： Venkat Subramaniam VENKATARAMANI ,  Anthony Christopher MARIN ,  Neelesh Nandkumar SARAWATE ,  Stephen Francis BANCHERI ,  Larry Steven ROSENZWEIG

IPC: C23C4/11 ,  C23C4/134 ,  C23C4/18 ,  F02C7/28

Abstract: Various embodiments include a gas turbine seal and methods of forming such seal. The method of forming the seal includes forming a freestanding ceramic seal for sealing in a gas turbine by applying a ceramic material on a substrate to form a ceramic layer, removing the substrate from the ceramic layer and finishing the ceramic layer to define the freestanding ceramic seal. The method includes depositing particles of the ceramic material in one of a molten or vapor state on a surface of the substrate and quenching the ceramic material to form the ceramic layer. The ceramic material comprises yttria-stabilized zirconia having a t′ tetragonal structure. A gas turbine including the freestanding ceramic seal is additionally disclosed.

公开(公告)号：US20170058686A1

公开(公告)日：2017-03-02

申请号：US14834866

申请日：2015-08-25

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Stephen Francis BANCHERI ,  Venkat Subramaniam VENKATARAMANI ,  Glen Harold KIRBY ,  Neelesh Nandkumar SARAWATE ,  Nicholas Edward ANTOLINO ,  Edip SEVINCER ,  Anthony Christopher MARIN

IPC: F01D11/00 ,  F01D25/00

CPC classification number: F01D11/003 ,  B05D1/005 ,  F01D9/041 ,  F01D11/005 ,  F01D25/005 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2240/80 ,  F16J15/0887 ,  Y02T50/672

Abstract: A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.

Abstract translation: 一种用于涡轮机械的涂覆密封槽系统包括第一涡轮机部件，该第一涡轮机部件包括第一凹槽，该第一凹槽具有连接到第一涡轮机部件的第一凹槽的至少一部分的至少一个第一涂层，第二涡轮部件，其包括具有至少一个 第二涂层附着到第二涡轮机部件的第二凹槽的至少一部分。 第一和第二涡轮机部件是彼此相邻的，第一凹槽具有第一涂层，第二凹槽具有第二涂层，一起形成延伸穿过第一涡轮机部件和第二涡轮机部件之间的间隙的涂覆的密封槽。 密封件在涂覆的密封槽中是一次性的，并且可以跨越第一和第二涡轮机部件之间的间隙延伸并且可与第一涂层和第二涂层接合以抑制气体通过间隙的泄漏。

公开(公告)号：US20170030211A1

公开(公告)日：2017-02-02

申请号：US14810672

申请日：2015-07-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Anthony Christopher MARIN ,  Venkat Subramaniam VENKATARAMANI ,  Neelesh Nandkumar SARAWATE ,  Edip SEVINCER

IPC: F01D11/00 ,  F16J15/08

Abstract: The present application provides slot seals for reducing leakages between adjacent components of turbomachinery. The seals may include a metallic shim and a coating overlying the metallic shim. The coating may be a metallic coating, a glass coating, an enamel coating or a ceramic coating. The coating may form an outer surface of the seal for engagement with seal slot surfaces of a seal slot of a turbomachine. The coating may be operable to conform to surface irregularities of the seal slot surfaces and remain coupled to the metallic shim at a predefined operating temperature and a predefined operating pressure to reduce leakage past the seal and thereby between the components. The coating may be configured to flow into depressions formed by the surface irregularities of the seal slot surfaces and remain coupled to the metallic shim at the predefined operating temperature and the predefined operating pressure.

Abstract translation: 本申请提供了槽密封件，用于减少涡轮机械的相邻部件之间的泄漏。 密封件可以包括金属垫片和覆盖金属垫片的涂层。 涂层可以是金属涂层，玻璃涂层，搪瓷涂层或陶瓷涂层。 涂层可以形成密封件的外表面，用于与涡轮机的密封槽的密封槽表面接合。 涂层可操作以符合密封槽表面的表面凹凸，并且在预定的操作温度和预定的操作压力下保持与金属垫片耦合，以减少经过密封件之间以及从而在组件之间的泄漏。 涂层可以被配置为流入由密封槽表面的表面不规则形成的凹陷中，并在预定义的操作温度和预定的操作压力下保持与金属垫片耦合。

公开(公告)号：US20160312635A1

公开(公告)日：2016-10-27

申请号：US14695288

申请日：2015-04-24

Applicant: General Electric Company

Inventor： Neelesh Nandkumar SARAWATE ,  Edip SEVINCER ,  Anthony MARIN

IPC: F01D11/00 ,  F01D25/00

CPC classification number: F01D11/005 ,  F01D25/005 ,  F05D2300/6033

Abstract: Seal assemblies for reducing leakage between components of turbomachinery are provided. The seals may include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, non-metallic end blocks and ceramic fiber are coupled. The end blocks may be configured to account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be made from a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks may protect the metallic shim from reaching potentially harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.

Abstract translation: 提供了用于减少涡轮机械部件之间的泄漏的密封组件。 密封件可以包括金属垫片，至少一对非金属端块和位于垫片和端块之间的陶瓷纤维。 垫片可以与端块机械地联接，使得金属垫片，非金属端块和陶瓷纤维被联接。 端块可以被配置为通过确保密封件与部件的密封接合来考虑涡轮机部件的未对准。 端块可以由陶瓷或玻璃材料制成，并且陶瓷纤维可以是高温编织陶瓷纤维。 陶瓷纤维和/或端块可以在使用密封件期间保护金属垫片免于达到可能有害的温度，例如在包括CMC部件的高温涡轮机中使用。

公开(公告)号：US20160312633A1

公开(公告)日：2016-10-27

申请号：US14695649

申请日：2015-04-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Edip SEVINCER ,  Neelesh Nandkumar SARAWATE ,  Anthony MARIN ,  Venkat Subramanian VENKATARAMANI

IPC: F01D11/00 ,  F01D25/00

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/005 ,  F05D2300/6012 ,  F05D2300/6033

Abstract: The present application provides composite seals for reducing leakages between adjacent components of turbomachinery. The composite seals may include a metallic shim, a metallic support structure and a ceramic, glass or enamel coating. The shim and the support structure may be bonded or fused together. The support structure may include internal voids or gaps, and the coating may be applied to the shim and the support structure such that the coating is provided within the voids or gaps of the support structure, between portions of the support structure and the shim, and substantially over the outer surface of the support structure. The support structure may thereby provide a mechanical attachment between the shim and the coating. In use, the coating provides thermal and/or chemical insulation to the metallic shim and the support structure of the seal.

Abstract translation: 本申请提供了用于减少涡轮机械的相邻部件之间的泄漏的复合密封件。 复合密封件可以包括金属垫片，金属支撑结构和陶瓷，玻璃或搪瓷涂层。 垫片和支撑结构可以结合或熔合在一起。 支撑结构可以包括内部空隙或间隙，并且可以将涂层施加到垫片和支撑结构，使得涂层设置在支撑结构的空隙或间隙内，支撑结构的部分和垫片之间，以及 基本上在支撑结构的外表面上。 因此，支撑结构可以在垫片和涂层之间提供机械连接。 在使用中，涂层为金属垫片和密封件的支撑结构提供热和/或化学绝缘。

公开(公告)号：US20160177757A1

公开(公告)日：2016-06-23

申请号：US14578816

申请日：2014-12-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Neelesh Nandkumar SARAWATE ,  Kirk D. GALLIER

IPC: F01D9/02 ,  F01D25/00 ,  F01D9/04

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.

Abstract translation: 翼型轮廓形密封件在中空翼型体的内表面和密封支架之间是一次性的。 密封件包括限定大体上闭合的曲线的细长构件，该曲线具有大致直的部分，大体上弯曲的部分，并且具有跨越并且沿着细长构件的长度的实心横截面。 当密封件设置在邻近中空翼型件本体的内表面的密封支撑件的翼型轮廓形状的槽中时，密封件一侧的流体压力大于密封件另一侧上的流体压力 密封件的一部分接合中空翼型体的内表面和凹槽的表面以形成密封，以防止流体从一侧泄漏到另一侧。