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公开(公告)号：US10746222B2
公开(公告)日：2020-08-18
申请号：US15135908
申请日：2016-04-22
Applicant: General Electric Company
Inventor： Tod Robert Steen , Charles Stanley Orkiszewski
Abstract: A damper assembly includes a bearing assembly including a radially outer surface. A housing surrounds the bearing assembly and includes a radially inner surface facing the radially outer surface. The radially outer and inner surfaces define a plurality of annuli therebetween. The damper assembly further includes a plurality of fluid supplies coupled in flow communication with the plurality of annuli and configured to deliver a fluid to each annulus of the plurality of annuli. Each fluid supply of the plurality of fluid supplies independently controls the fluid within the respective annulus.
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公开(公告)号：US20190203646A1
公开(公告)日：2019-07-04
申请号：US15861780
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Andrew Bryan Cannella , Charles Stanley Orkiszewski , Milind Chandrakant Dhabade , Praveen Sharma , Brian Drummond , Shivam Mittal
Abstract: The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.
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公开(公告)号：US10718231B2
公开(公告)日：2020-07-21
申请号：US15843526
申请日：2017-12-15
Applicant: General Electric Company
Inventor： Charles Stanley Orkiszewski
IPC: F01D19/02 , F04D29/66 , F01D25/34 , F01D5/02 , F04D29/52 , F16D43/30 , F16D43/04 , F01D19/00 , F02C7/268 , F02C7/26 , F02C7/277
Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.
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公开(公告)号：US20190169992A1
公开(公告)日：2019-06-06
申请号：US15832859
申请日：2017-12-06
Applicant: General Electric Company
Inventor： Jorg Arrien Tiemon , Charles Stanley Orkiszewski
IPC: F01D5/14
Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.
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公开(公告)号：US11485508B2
公开(公告)日：2022-11-01
申请号：US16667319
申请日：2019-10-29
Applicant: General Electric Company
IPC: B64D27/26 , F01D25/04 , F01D25/16 , F01D5/10 , B64D27/10 , B64D29/00 , B64D35/02 , F01D15/12 , F01D25/24
Abstract: A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.
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Patent Agency Ranking
公开(公告)号：US10760498B2
公开(公告)日：2020-09-01
申请号：US15861780
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Andrew Bryan Cannella , Charles Stanley Orkiszewski , Milind Chandrakant Dhabade , Praveen Sharma , Brian Drummond , Shivam Mittal
Abstract: The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.
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公开(公告)号：US10518891B2
公开(公告)日：2019-12-31
申请号：US14943653
申请日：2015-11-17
Applicant: General Electric Company
IPC: B64D27/26 , F01D5/10 , F01D25/04 , F01D25/16 , B64D27/10 , B64D29/00 , B64D35/02 , F01D15/12 , F01D25/24
Abstract: A turbine engine assembly is provided. The assembly includes a stationary component, a drive shaft, and a gearbox coupled along the drive shaft, and coupled to the stationary component. The assembly also includes a vibration-reducing mechanism coupled between the stationary component and the gearbox. The vibration-reducing mechanism is configured to isolate a vibratory response of the gearbox from the stationary component.
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公开(公告)号：US11542820B2
公开(公告)日：2023-01-03
申请号：US15832859
申请日：2017-12-06
Applicant: General Electric Company
Inventor： Jorg Arrien Tiemon , Charles Stanley Orkiszewski
Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.
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公开(公告)号：US20190186296A1
公开(公告)日：2019-06-20
申请号：US15843588
申请日：2017-12-15
Applicant: General Electric Company
Inventor： Charles Stanley Orkiszewski
CPC classification number: F01D25/164 , F01D25/18 , F05D2220/323 , F05D2240/50 , F05D2260/98 , F05D2270/303 , F05D2270/42 , F05D2270/44 , F16C27/045 , F16C2360/23
Abstract: Dampers for bearing assemblies of gas turbine engines are provided. For example, a damper comprises a damper housing, a lubricant passage defined in the damper housing, and a valve positioned within the lubricant passage. The lubricant passage includes an inlet and an outlet. In one embodiment, the valve is configured to restrict a flow of lubricant from the inlet into the damper when a reference temperature is below a threshold temperature. In another embodiment, the valve is configured to increase leakage of a lubricant through the outlet when a reference temperature is below a threshold temperature. In other embodiments, the valve is passively actuated and is configured to move within the lubricant passage to control a flow of lubricant from the inlet to the outlet based on a reference temperature.
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公开(公告)号：US20190186284A1
公开(公告)日：2019-06-20
申请号：US15843526
申请日：2017-12-15
Applicant: General Electric Company
Inventor： Charles Stanley Orkiszewski
Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.
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