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公开(公告)号：US20200263550A1
公开(公告)日：2020-08-20
申请号：US16280596
申请日：2019-02-20
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Thomas Ory Moniz
Abstract: A gas turbine engine includes a compressor and a turbine; a plurality of rotor blades positioned in the compressor or the turbine and arranged in a plurality of stages along an axial direction; an outer drum positioned at least partially radially outward of the plurality of rotor blades and rotatable with the plurality of rotor blades; and a casing extending over the outer drum and defining a plurality of air cavities with the outer drum, the plurality of air cavities arranged in series airflow communication along the axial direction.
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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：US10663036B2
公开(公告)日：2020-05-26
申请号：US15621496
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Darek Tomasz Zatorski
IPC: F16H1/22 , F16H57/033 , H02K7/08 , F01D25/16 , F02C7/36
Abstract: The present disclosure is directed to a gas turbine engine, wherein the gas turbine engine defines a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline extended along the longitudinal direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes an annular stationary turbine frame centered around the axial centerline; an engine shaft extended generally along the longitudinal direction; an input shaft extended generally along the longitudinal direction; and a gear assembly including a first gear coupled to the input shaft, a second gear coupled to the turbine frame, and an inner spool coupling the first gear and the second gear, in which the inner spool defines a gear axis extended therethrough. The inner spool, the first gear, and the second gear are together rotatable about the gear axis. The gear axis is rotatable about the axial centerline of the engine. The gas turbine engine further includes a housing coupled to the inner spool and the engine shaft.
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公开(公告)号：US20200003157A1
公开(公告)日：2020-01-02
申请号：US16535930
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Jeffrey Donald Clements , Darek Tomasz Zatorski , Alan Roy Stuart
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section, a gearbox proximate to the turbine section, and a driveshaft. The turbine section includes a first rotating component interdigitated with a second rotating component along the longitudinal direction. The first rotating component includes an outer shroud defining a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction and one or more connecting airfoils coupling the outer shroud to a radially extended rotor. The second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to an input shaft connected to an input gear of the gearbox. The driveshaft is extended in the longitudinal direction and is connected to an output gear of the gearbox. The first rotating component is coupled to the driveshaft.
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公开(公告)号：US10480322B2
公开(公告)日：2019-11-19
申请号：US15870313
申请日：2018-01-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.
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Patent Agency Ranking
公开(公告)号：US10465538B2
公开(公告)日：2019-11-05
申请号：US14873324
申请日：2015-10-02
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Patrick John Lonneman , Alan Roy Stuart
Abstract: A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct for airflow generated by the fan. The fan cowl includes an aft edge that defines a physical flow area of the bypass duct, and a deflection device configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.
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公开(公告)号：US20180355951A1
公开(公告)日：2018-12-13
申请号：US15621496
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Darek Tomasz Zatorski
IPC: F16H1/22 , F16H57/033 , H02K7/08
CPC classification number: F16H1/22 , F01D25/162 , F02C7/36 , F05D2260/40311 , F16H57/033 , F16H2057/0335 , H02K7/083
Abstract: The present disclosure is directed to a gas turbine engine, wherein the gas turbine engine defines a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline extended along the longitudinal direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes an annular stationary turbine frame centered around the axial centerline; an engine shaft extended generally along the longitudinal direction; an input shaft extended generally along the longitudinal direction; and a gear assembly including a first gear coupled to the input shaft, a second gear coupled to the turbine frame, and an inner spool coupling the first gear and the second gear, in which the inner spool defines a gear axis extended therethrough. The inner spool, the first gear, and the second gear are together rotatable about the gear axis. The gear axis is rotatable about the axial centerline of the engine. The gas turbine engine further includes a housing coupled to the inner spool and the engine shaft.
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58.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：US20180328287A1
公开(公告)日：2018-11-15
申请号：US15593748
申请日：2017-05-12
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , James William Simunek , Jeffrey Donald Clements , Brandon Wayne Miller , Sridhar Adibhatla
CPC classification number: F02C7/36 , F02C3/067 , F02C7/22 , F02C9/20 , F04D29/563 , F05D2220/32 , F05D2270/304 , F05D2270/31
Abstract: The present disclosure is directed to a method of control of a gas turbine engine comprising a fan section coupled to a low turbine together defining a low spool, an intermediate compressor coupled to an intermediate turbine together defining an intermediate spool, and a high compressor coupled to a high turbine together defining a high spool. The method includes providing an intermediate spool speed to low spool speed characteristic curve to a controller; providing a commanded power output to the controller; providing one or more of an environmental condition to the controller; determining, via the controller, a commanded fuel flow rate; determining, via the controller, a commanded intermediate compressor loading; and generating an actual power output of the engine, wherein the actual power output is one or more of an actual low spool speed, an actual intermediate spool speed, an actual high spool speed, and an actual engine pressure ratio.
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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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