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公开(公告)号：US11814988B2
公开(公告)日：2023-11-14
申请号：US17475585
申请日：2021-09-15
Inventor： Rodrigo Rodriguez Erdmenger , Rudolph Selmeier , Mehdi Milani Baladi , Jacek Marian Elszkowski
CPC classification number: F01D9/041 , F01D9/045 , F01D17/105 , F05D2240/12 , F05D2260/606
Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.
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公开(公告)号：US20220090507A1
公开(公告)日：2022-03-24
申请号：US17475585
申请日：2021-09-15
Inventor： Rodrigo Rodriguez Erdmenger , Rudolph Selmeier , Mehdi Milani Baladi , Jacek Marian Elszkowski
IPC: F01D9/04
Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.
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公开(公告)号：US20200166143A1
公开(公告)日：2020-05-28
申请号：US16201669
申请日：2018-11-27
Applicant: General Electric Company
Inventor： Quang Tue Nguyen Tran , Nathan Evan McCurdy Gibson , Rodrigo Rodriguez Erdmenger , Christopher Edward Wolfe , Steven Douglas Johnson , Antonio Guijarro Valencia
Abstract: A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing.
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公开(公告)号：US20230287797A1
公开(公告)日：2023-09-14
申请号：US17691380
申请日：2022-03-10
Inventor： Antonio Guijarro Valencia , Rodrigo Rodriguez Erdmenger , Rahul Anil Bidkar , Scott Alan Schimmels , Tran Quang Tue Nguyen
IPC: F01D11/16
CPC classification number: F01D11/16 , F05D2240/58 , F05D2260/608
Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.
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公开(公告)号：US20210108730A1
公开(公告)日：2021-04-15
申请号：US17128422
申请日：2020-12-21
Applicant: General Electric Company
Inventor： Rahul Anil Bidkar , Christopher Edward Wolfe , Nathan Evan McCurdy Gibson , Rodrigo Rodriguez Erdmenger , Deepak Trivedi , Quang Tue Nguyen Tran
Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.
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Patent Agency Ranking
公开(公告)号：US10428673B2
公开(公告)日：2019-10-01
申请号：US15143878
申请日：2016-05-02
Applicant: General Electric Company
Abstract: An aspirating face seal assembly for a turbo-machine including a rotor assembly having a first radially extending portion defining a rotor surface is disclosed. The aspirating face seal assembly includes a seal body including a second radially extending portion defining a bearing surface and having a plurality of return channels. The second radially extending portion is disposed in the turbo-machine such that the bearing surface is disposed facing the rotor surface. The aspirating face seal assembly further includes an annular ring including one or more openings. The annular ring is concentrically disposed on the second radially extending portion and between the rotor surface and the second radially extending portion and configured to rotate in an event of rub between the first radially extending portion and the annular ring. A turbo-machine including the aspirating face seal assembly and a method for operating an aspirating face seal are also disclosed.
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公开(公告)号：US20170328234A1
公开(公告)日：2017-11-16
申请号：US15155823
申请日：2016-05-16
Applicant: General Electric Company
Inventor： Rodrigo Rodriguez Erdmenger , Sebastian Walter Freund , Ismail Hakki Sezal , Aneesh Sridhar Vadvadgi
CPC classification number: F01D17/141 , F01D9/041 , F01D9/045 , F01D17/148 , F01D25/24 , F02B33/40 , F02B39/16 , F05D2220/40 , F05D2240/128 , F05D2250/90
Abstract: A nozzle assembly of a turbocharger includes a nozzle and a ring-shaped body. The nozzle has flow passages extending through the nozzle and configured to direct air received from a volute housing of the turbocharger through the nozzle to turbine blades of the turbocharger. The ring-shaped body is coupled with the nozzle and is configured to rotate around the nozzle. The ring-shaped body includes blocking segments that block the flow of the air and openings between the blocking segments that permit the air to flow through the ring-shaped body. The ring-shaped body is configured to rotate relative to the nozzle to change how many of the flow passages in the nozzle are blocked by the blocking segments of the ring-shaped body.
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公开(公告)号：US20170268528A1
公开(公告)日：2017-09-21
申请号：US15075339
申请日：2016-03-21
Applicant: General Electric Company
Inventor： Rodrigo Rodriguez Erdmenger , Vittorio Michelassi
CPC classification number: F04D29/30 , F04D29/284 , F04D29/4206
Abstract: Centrifugal compressor having flow-control blades in which each of the flow-control blades has a pressure side and an opposite suction side. Each of the flow-control blades includes a main section and an inducer section that project away from an impeller surface. The inducer section is positioned upstream from the main section. The inducer section includes a trailing edge and the main section includes a leading edge that is spaced apart from the trailing edge. The inducer sections are aligned with the respective main sections as the inducer and main sections project from the impeller surface to a designated point above the impeller surface. Each of the trailing edges of the inducer sections and the respective leading edge of the main section form a bleed gap therebetween after the designated point. The bleed gap is configured to permit fluid to flow therethrough from the pressure side to the suction side.
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公开(公告)号：US20170022837A1
公开(公告)日：2017-01-26
申请号：US14807376
申请日：2015-07-23
Applicant: General Electric Company
CPC classification number: F01D5/046 , F01D5/048 , F01D11/025 , Y02E20/14 , Y02T50/673
Abstract: An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface.
Abstract translation: 提供了一种用于涡轮发动机的吸气密封组件。 抽吸密封组件包括面密封件和旋转部件。 所述面密封件包括第一环形密封表面，并且所述旋转部件包括邻近所述第一环形密封表面定位并且在其之间限定密封接合的第二环形密封表面。 面密封件构造成朝向密封界面排出空气流。 密封组件还包括在第一和第二环形密封表面之间延伸的第一密封构件，使得空气流引导穿过密封界面的背压，以及从第一密封构件径向向内定位并在第一密封构件之间延伸的第二密封构件 第一和第二环形密封表面。 选择第二密封构件的长度以增加在密封界面上引起的背压。
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公开(公告)号：US12209533B2
公开(公告)日：2025-01-28
申请号：US18176246
申请日：2023-02-28
Applicant: General Electric Company
Inventor： Rodrigo Rodriguez Erdmenger , David Raju Yamarthi , Maysaa Rizk , David Justin Brady , Adam Joseph Wangler , Ismail Hakki Sezal , Michael Joseph Murray
Abstract: Apparatus, systems, and articles of manufacture are disclosed to power thermal management systems with heat of a working fluid therein. Example thermal management system include: a thermal transport bus loop fluidly coupled to at least one heat source exchanger and at least one heat sink exchanger; a turbomachine including a turbine and a compressor, the turbine and compressor rotatably interlocked via a shaft, the compressor coupled to the thermal transport bus loop, the turbine including an inlet and an outlet, the inlet connected to a first point of the thermal transport bus loop via a first flowline, the outlet connected to a second point of the thermal transport bus loop via a second flowline; and a control valve coupled to the first flowline, the control valve to adjust a mass flowrate of the heat exchange fluid in the first flowline based on a speed of the shaft.
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