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公开(公告)号：US12123306B2
公开(公告)日：2024-10-22
申请号：US17851672
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Deepak Trivedi , Rahul Anil Bidkar , Bugra Han Ertas
CPC classification number: F01D11/08 , F05D2220/323 , F05D2240/55
Abstract: A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.
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公开(公告)号：US20240060458A1
公开(公告)日：2024-02-22
申请号：US17890572
申请日：2022-08-18
Applicant: General Electric Company
Inventor： Bugra Han Ertas , Trevor Howard Wood
CPC classification number: F02K1/763 , F02K1/72 , F05D2220/323 , F05D2260/50
Abstract: A cascade thrust reverser assembly is provided for a turbofan engine. The turbofan engine includes a nacelle assembly defining a bypass passage, and the cascade thrust reverser assembly includes at least one cascade assembly configured to be at least partially enclosed by the nacelle assembly. The cascade assembly may further include a plurality of cascade segments and an actuation assembly operably connected to the plurality of cascade segments, wherein the actuation assembly is configured to increase an axial extent of the cascade assembly and rotate the plurality of cascade segments.
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公开(公告)号：US20230417148A1
公开(公告)日：2023-12-28
申请号：US17851672
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Deepak Trivedi , Rahul Anil Bidkar , Bugra Han Ertas
IPC: F01D11/08
CPC classification number: F01D11/08 , F05D2220/323 , F05D2240/55
Abstract: A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.
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公开(公告)号：US20230407517A1
公开(公告)日：2023-12-21
申请号：US17843286
申请日：2022-06-17
Applicant: General Electric Company
Inventor： Andrew Lee Trimmer , John Malott Cottrill , Douglas Carl Hofer , Bugra Han Ertas
Abstract: Methods and systems of electrochemically machining a component are provided. The method may include applying two or more potentials to a tool electrode comprising an array of two or more individual electrodes to generate two or more electric fields in between the tool electrode and a workpiece opposite of the tool electrode, wherein each of the two or more electric fields is generated by one of the array of two or more individual electrodes.
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公开(公告)号：US11492910B2
公开(公告)日：2022-11-08
申请号：US16697406
申请日：2019-11-27
Applicant: General Electric Company
Inventor： Peeyush Pankaj , Narayanan Payyoor , Richard Schmidt , Bugra Han Ertas
Abstract: A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.
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Patent Agency Ranking
公开(公告)号：US11193385B2
公开(公告)日：2021-12-07
申请号：US15131154
申请日：2016-04-18
Applicant: General Electric Company
Abstract: A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.
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公开(公告)号：US10816078B2
公开(公告)日：2020-10-27
申请号：US16136829
申请日：2018-09-20
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , Donald Albert Bradley , Bugra Han Ertas
Abstract: A planet gear train for an engine casing includes a sun gear rotatable by a shaft, a ring gear, a plurality of planet gears rotatably mounted in a planet carrier and meshing with the sun gear and the ring gear, and a damping system. The damping system includes a soft mount disposed about the shaft and coupling the planet carrier the engine casing. The soft mount includes a flexible inner sleeve and a flexible outer sleeve. The flexible inner sleeve and the flexible outer sleeve are fixedly coupled together at respective central portions thereof near the shaft. The damping system further includes a plurality of damping couplers disposed about an outer flange of the planet carrier. The plurality of damping couplers is configured to flexibly couple the flexible inner sleeve to the flexible outer sleeve.
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公开(公告)号：US10711877B2
公开(公告)日：2020-07-14
申请号：US15903110
申请日：2018-02-23
Applicant: General Electric Company
Inventor： Kenneth Lee Fisher , George Hanna Ghanime , Bugra Han Ertas , Darren Lee Hallman
Abstract: A gearbox assembly for a gas turbine engine used in an aircraft having passive lubrication capabilities during wind milling includes a gearbox housing, a gear train assembly housed within the gearbox housing, a lubricant in the gearbox housing for lubricating the gear train assembly, and a first scavenge port formed in the gearbox housing. The first scavenge port is changeable between an open position and a closed position. Further, the first scavenge port remains in the open position during normal operation of the gas turbine engine to allow the lubricant to drain from the gearbox housing. Upon occurrence of a loss of lubricant pressure in the gearbox assembly, the first scavenge port is changed to the closed position to trap at least a portion of the lubricant in the gearbox housing. Thus, the trapped lubricant provides passive lubrication to the gear train assembly during the loss of lubricant pressure.
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公开(公告)号：US20200056677A1
公开(公告)日：2020-02-20
申请号：US16103314
申请日：2018-08-14
Applicant: General Electric Company
Inventor： Richard Schmidt , Bugra Han Ertas , Weize Kang
Abstract: A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.
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公开(公告)号：US10508731B2
公开(公告)日：2019-12-17
申请号：US15399291
申请日：2017-01-05
Applicant: General Electric Company
Inventor： Darren Lee Hallman , Donald Albert Bradley , Changjie Sun , Bugra Han Ertas
Abstract: A planet gear includes a pin and an annular planet gear rim. The pin has a pin radius. The pin includes a pin outer surface. The annular planet gear rim has an inner radius and an outer radius. The annular planet gear rim includes an inner surface and an outer surface. The inner surface and the pin outer surface define a clearance therebetween. The clearance is greater than 0 when a radial force is applied to the planet gear.
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