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公开(公告)号：US20140271142A1
公开(公告)日：2014-09-18
申请号：US13827762
申请日：2013-03-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joseph C. Albers , Monty Lee Shelton , Robert Proctor , Richard Russo, JR.
IPC: F01D25/24
CPC classification number: F01D11/122 , F01D11/005 , F01D11/127 , F01D25/246 , F02C7/28 , F05D2220/32 , F05D2240/11 , F05D2240/57 , Y02T50/671
Abstract: A turbine shroud assembly comprises a honeycomb rub strip, a metallic backsheet disposed along an upper edge of said honeycomb seal structure, a shroud frame having a first rail and a second rail disposed at lateral edges of said metallic backsheet, a first support and a second support connected to the first rail and the second rail, a spline extending axially in the first rail and the second rail along laterally outer surfaces of the first rail and the second rail and, a spline seal having a first edge and a second opposite edge, the first edge disposed in each of the spline grooves and the second opposite edge being capable of positioning in an adjacent shroud assembly.
Abstract translation: 涡轮机罩组件包括蜂窝状擦拭条，沿着所述蜂窝密封结构的上边缘设置的金属底片，具有设置在所述金属底片的侧边缘处的第一轨道和第二轨道的护罩框架，第一支撑件和第二支撑件 连接到第一轨道和第二轨道的支撑件，沿第一轨道和第二轨道的横向外表面在第一轨道和第二轨道中轴向延伸的花键，以及具有第一边缘和第二相对边缘的花键密封件， 设置在每个花键槽中的第一边缘和第二相对边缘能够定位在相邻的护罩组件中。
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公开(公告)号：US20140140833A1
公开(公告)日：2014-05-22
申请号：US13683813
申请日：2012-11-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joseph Charles Albers , Robert Proctor , Monty Lee Shelton , Richard Russo, JR.
CPC classification number: F01D25/28 , F01D5/12 , F01D5/225 , F01D11/122 , F01D11/127
Abstract: A turbine shroud apparatus for a gas turbine engine having a centerline axis includes: a shroud segment having: an arcuate body extending axially between forward and aft ends and laterally between opposed end faces, wherein each of the end faces includes seal slots formed therein; and an arcuate stationary seal member mounted to the body; a turbine vane disposed axially aft of the shroud segment; and a casing surrounding the shroud segment and the turbine vane; wherein the turbine vane is mounted to the case so as to bear against the stationary seal member, compressing it and forcing the shroud segment radially outward against the casing.
Abstract translation: 一种具有中心轴线的燃气涡轮发动机的涡轮机护罩装置，包括：护罩段，其具有：在前端和后端之间轴向延伸并且在相对的端面之间横向延伸的弧形体，其中每个端面包括形成在其中的密封槽; 以及安装在所述主体上的弧形固定密封构件; 设置在所述护罩段的轴向后方的涡轮叶片; 以及围绕所述护罩段和所述涡轮叶片的壳体; 其中所述涡轮叶片安装到所述壳体上以便抵靠所述固定密封构件，将所述涡轮叶片压缩并迫使所述护罩段径向向外抵靠所述壳体。
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公开(公告)号：US20230265764A1
公开(公告)日：2023-08-24
申请号：US18297835
申请日：2023-04-10
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.
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公开(公告)号：US11359646B2
公开(公告)日：2022-06-14
申请号：US16555558
申请日：2019-08-29
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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公开(公告)号：US11187094B2
公开(公告)日：2021-11-30
申请号：US16550363
申请日：2019-08-26
Applicant: General Electric Company
Inventor： Kevin Robert Feldmann , Robert Proctor , David Scott Stapleton , Robert Charles Groves, II
Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.
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Patent Agency Ranking
公开(公告)号：US11033845B2
公开(公告)日：2021-06-15
申请号：US15314536
申请日：2015-05-29
Applicant: General Electric Company
Inventor： Timothy Deryck Stone , Gregory Michael Laskowski , Robert Proctor , Curtis Stover , Robert Francis Manning , Victor Hugo Silva Correia , Jared Peter Buhler , Robert Carl Murray , Corey Bourassa, Jr. , Byron Andrew Pritchard , Jonathan Russell Ratzlaff
IPC: B01D45/16 , F02C7/18 , B04C3/06 , F02C6/08 , F01D5/18 , F01D9/06 , F02C7/052 , B04C3/00 , F02K3/04
Abstract: A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.
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公开(公告)号：US10781709B2
公开(公告)日：2020-09-22
申请号：US15865359
申请日：2018-01-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Nathan Evan McCurdy Gibson , Robert Proctor , Bhaskar Nanda Mondal , Steven Douglas Johnson
Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.
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公开(公告)号：US10690055B2
公开(公告)日：2020-06-23
申请号：US15314490
申请日：2015-05-27
Applicant: General Electric Company
Inventor： Curtis Walton Stover , Jonathan Michael Rausch , Satoshi Atsuchi , Gulcharan Singh Brainch , Robert David Briggs , Ronald Scott Bunker , Ambarish Jayant Kulkarni , Michael Alan Meade , Byron Andrew Pritchard , Robert Proctor
Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.
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公开(公告)号：US20190218913A1
公开(公告)日：2019-07-18
申请号：US15870313
申请日：2018-01-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.
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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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