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公开(公告)号：US20210199051A1
公开(公告)日：2021-07-01
申请号：US16730570
申请日：2019-12-30
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , Robert Proctor , Christopher Michael Thompson , Scott Alan Schimmels , Steven Douglas Johnson
IPC: F02C7/18
Abstract: An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.
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公开(公告)号：US20210123358A1
公开(公告)日：2021-04-29
申请号：US16666561
申请日：2019-10-29
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Robert Proctor
IPC: F01D11/00
Abstract: An airfoil assembly and method for an engine comprising a plurality of circumferentially arranged platforms having confronting end faces each platform defining a base portion from which an airfoil extends outwardly defining a radial direction and from which a set of legs extends radially inward, a disk post coupled to at least one leg of the set of legs, a cavity formed by the platform, set of legs, and the disk post defining a static pressure zone during operation, a high pressure zone located exteriorly of the cavity; and at least one blocking spline seal.
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公开(公告)号：US10975731B2
公开(公告)日：2021-04-13
申请号：US15314341
申请日：2015-05-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Francis Manning , Timothy Deryck Stone , Jared Peter Buhler , Victor Hugo Silva Correia , Gregory Michael Laskowski , Robert Carl Murray , Jonathan Russell Ratzlaff , Robert Proctor , John Howard Starkweather , Curtis Walton Stover
IPC: B01D45/16 , F02C7/05 , F02C7/052 , F01D25/32 , B04C3/06 , B04C3/00 , B64D33/08 , F01D5/08 , F01D25/12 , F02C3/04 , F02C7/18 , F02C9/18 , B64D33/02
Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.
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公开(公告)号：US10794203B2
公开(公告)日：2020-10-06
申请号：US15466078
申请日：2017-03-22
Applicant: General Electric Company
Inventor： Sivaprakaash Karuppanchetty , Suresh Nukala Kumar , Robert Proctor
Abstract: A scavenge tube for conveying oil within an engine. The scavenge tube includes an outer tube and an inner tube. The outer tube defines a first surface and the inner tube defines a second surface. The inner tube is configured to be fluidly connected to a source for oil. A space that is defined between the outer tube and the inner tube such that the first surface opposes the second surface. A plurality of bumps is positioned within the space such that each bump extends from one of the first surface and the second surface and extends toward the opposing surface.
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公开(公告)号：US10480322B2
公开(公告)日：2019-11-19
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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Patent Agency Ranking
公开(公告)号：US20190211699A1
公开(公告)日：2019-07-11
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：US10125781B2
公开(公告)日：2018-11-13
申请号：US14984473
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Kevin Samuel Klasing , Robert Proctor , Jonathan Russell Ratzlaff , Thomas Matthew Doerflein
IPC: F02C6/08 , F04D27/00 , F04D29/32 , F04D29/52 , F01D9/06 , F02C9/18 , F04D27/02 , F01D17/10 , F04D29/54
Abstract: A compressor for a gas turbine engine includes a stator and a rotor. The stator includes first and second stator vanes attached to first and second vane platforms, respectively. The rotor includes a plurality of rotor blades that rotate with respect to the stator. An inner stator casing supports the first and second vane platforms and encloses the stator and the rotor. An outer stator casing encloses the inner stator casing, and a bleed cavity is disposed therebetween. At least one diffuser is disposed between the first vane platform and the second vane platform, and is configured to allow air communication between the inner stator casing and the bleed cavity. An exit opening of the diffuser is disposed within the bleed cavity at a location separate from the inner stator casing and the outer stator casing.
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公开(公告)号：US09238977B2
公开(公告)日：2016-01-19
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：US20130309079A1
公开(公告)日：2013-11-21
申请号：US13662284
申请日：2012-10-26
Applicant: General Electric Company
IPC: F01D25/00
CPC classification number: F01D9/041 , F01D5/189 , F01D25/00 , F05B2230/237 , F05D2240/81 , F05D2260/201 , Y02T50/676
Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
Abstract translation: 涡轮喷嘴段包括：弓形外带段; 所述翼型涡轮叶片从所述外带段径向向内延伸，所述涡轮叶片具有中空的内部; 冲击挡板组件，其固定到所述外部带，以便与所述外部带段协调地限定冲击腔，其中所述冲击挡板组件具有形成在其中的至少一个冲击孔，所述至少一个冲击孔被布置成在所述外部带段处引导冷却空气; 并且至少一个冲击插入件具有形成在其中的至少一个冲击孔，其设置在涡轮叶片的内部，冲击插入件与冲击挡板组件中的开口相配合，使得冲击挡板与冲击腔直接流体连通隔离 。
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20.发明授权公开(公告)号：US11673682B2
公开(公告)日：2023-06-13
申请号：US16941730
申请日：2020-07-29
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Thomas Kupiszewski , Paul Alexander Intemann , Robert Proctor
Abstract: A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.
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