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公开(公告)号：US09932858B2
公开(公告)日：2018-04-03
申请号：US14809560
申请日：2015-07-27
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Richard Schmidt , Daniel Alan Niergarth
CPC classification number: F01D25/164 , F01D9/065 , F01D25/162 , F01D25/18 , F01D25/20 , F02C7/32 , F05D2260/98 , Y02T50/671
Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.
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公开(公告)号：US12215633B2
公开(公告)日：2025-02-04
申请号：US18486523
申请日：2023-10-13
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
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公开(公告)号：US20210156256A1
公开(公告)日：2021-05-27
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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公开(公告)号：US11002335B2
公开(公告)日：2021-05-11
申请号：US15346202
申请日：2016-11-08
Applicant: General Electric Company
Inventor： Shuvajyoti Ghosh , Narayanan Payyoor , Surender Reddy Bhavanam , Richard Schmidt , Tod Robert Steen
IPC: B60K5/12 , F01D25/04 , F16F9/53 , F16F15/16 , F01D25/16 , F16F15/03 , F16C27/04 , F16C19/26 , F16F15/18
Abstract: A controllable magneto-rheological device includes an annular cylinder formed by inner and outer walls connected at first and second opposing ends and forming an inner shaft configured to receive an operational component of an engine, generator or other device including one or more rotating structures. A magneto-rheological fluid is provided to fill a volume between the inner and outer walls of the annular cylinder. A plurality of electro-magnetic coils are positioned around the outer wall of the annular cylinder. One or more current controllers are coupled to the plurality of electro-magnetic coils for introducing a current through each of the electro-magnetic coils and corresponding magnetic flux through the magneto-rheological fluid. A level of current provided to each of the plurality of electro-magnetic coils directly affects the viscosity of the magneto-rheological fluid and thus the stiffness and damping levels of the controllable magneto-rheological device.
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公开(公告)号：US10823001B2
公开(公告)日：2020-11-03
申请号：US15710146
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt , Bhaskar Nanda Mondal , Ramana Reddy Kollam
IPC: F01D25/16 , F01D5/30 , F02C3/04 , F02K3/04 , F02C3/067 , F02C7/06 , F02C3/107 , F02C3/113 , F02C7/36
Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.
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Patent Agency Ranking
公开(公告)号：US10718265B2
公开(公告)日：2020-07-21
申请号：US15605164
申请日：2017-05-25
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor comprising a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor comprising a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The first turbine bearing defines an outer air bearing along an outer diameter of the first turbine bearing and adjacent to the hub of the low speed turbine rotor. The first turbine bearing defines an inner air bearing along an inner diameter of the first turbine bearing and adjacent to the HP shaft.
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公开(公告)号：US20190085720A1
公开(公告)日：2019-03-21
申请号：US15710138
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt
CPC classification number: F01D25/16 , F01D5/30 , F01D25/164 , F02C3/04 , F02C3/067 , F02C7/06 , F02C7/32 , F02C7/36 , F02K3/04 , F05D2240/24 , F05D2240/40 , F05D2240/50 , F05D2260/4031
Abstract: A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.
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公开(公告)号：US20180347405A1
公开(公告)日：2018-12-06
申请号：US15611312
申请日：2017-06-01
Applicant: General Electric Company
Inventor： Richard Schmidt
CPC classification number: F01D25/285 , B64F5/60 , G01H1/003 , G01L5/133
Abstract: A compliant mounting adapter for mounting an engine to a test stand includes: a body having: a first mounting interface configured for being coupled to the test stand; a second mounting interface configured for being coupled to the engine, the second mounting interface spaced-away from the first mounting interface; and a spanning element interconnecting the first and second mounting interfaces. The body is sufficiently flexible so as to permit movement relative movement of the two mounting interfaces, in response to forces generated by engine operation, in at least two degrees of freedom, and has a predetermined stiffness in each of the at least two degrees of freedom, with the predetermined stiffness of each degree of freedom being substantially independent from the stiffness of the other degrees of freedom.
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19.发明申请公开(公告)号：US20180340423A1
公开(公告)日：2018-11-29
申请号：US15605351
申请日：2017-05-25
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
CPC classification number: F01D25/22 , F01D5/082 , F01D5/087 , F02C7/06 , F05D2240/53 , F05D2250/44
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, an axial centerline extended along the longitudinal direction, an upstream end and a downstream end opposite of the upstream end along the longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes a high speed turbine rotor coupled to a high pressure (HP) shaft and HP compressor, a low speed turbine rotor comprising an axially extended hub, and a first turbine bearing disposed radially between the low speed turbine rotor and the high speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit through the high speed turbine rotor. The low speed turbine rotor includes a rotating nozzle adjacent to the turbine cooling conduit. The first turbine bearing defines an outer air bearing and an inner air bearing. The first turbine bearing defines a stationary nozzle adjacent to the rotating nozzle of the first turbine rotor.
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公开(公告)号：US20180274365A1
公开(公告)日：2018-09-27
申请号：US15412157
申请日：2017-01-23
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section that includes a first rotating component and a second rotating component. The first rotating component includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction. The outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction. The first rotating component further includes at least one connecting airfoil coupling the inner shroud and the outer shroud. The second rotating component is upstream of the one or more connecting airfoils of the first rotating component along the longitudinal direction. The second rotating component includes a plurality of second airfoils extended outward in the radial direction. The first rotating component defines at least one stage of the plurality of outer shroud airfoils upstream of the second rotating component.
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