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公开(公告)号：US20170307046A1
公开(公告)日：2017-10-26
申请号：US15135908
申请日：2016-04-22
Applicant: General Electric Company
Inventor： Tod Robert Steen , Charles Stanley Orkiszewski
IPC: F16F15/023 , F01D25/16 , F01D25/04
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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Patent Agency Ranking
公开(公告)号：US11187102B2
公开(公告)日：2021-11-30
申请号：US16931857
申请日：2020-07-17
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：US10947993B2
公开(公告)日：2021-03-16
申请号：US15822507
申请日：2017-11-27
Applicant: General Electric Company
Inventor： Kudum Shinde , Praveen Sharma , Shashank Suresh Puranik , Shivam Mittal , Charles Stanley Orkiszewski , Carl Lawrence MacMahon , Anthony Michael Metz , Brian Drummond
Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal circuit at the second manifold assembly.
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公开(公告)号：US10801361B2
公开(公告)日：2020-10-13
申请号：US15260641
申请日：2016-09-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nagamohan Govinahalli Prabhakar , Steven Andrew Strang , Charles Stanley Orkiszewski , Subramanya Shankar , Nitesh Jain , Michael Riehle
Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.
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公开(公告)号：US20190162203A1
公开(公告)日：2019-05-30
申请号：US15822507
申请日：2017-11-27
Applicant: General Electric Company
Inventor： Kudum Shinde , Praveen Sharma , Shashank Suresh Puranik , Shivam Mittal , Charles Stanley Orkiszewski , Carl Lawrence MacMahon , Anthony Michael Metz , Brian Drummond
Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal circuit at the second manifold assembly.
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公开(公告)号：US20180073388A1
公开(公告)日：2018-03-15
申请号：US15260641
申请日：2016-09-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nagamohan Govinahalli Prabhakar , Steven Andrew Strang , Charles Stanley Orkiszewski , Subramanya Shankar , Nitesh Jain , Michael Riehle
Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.
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