General Electric Company patent applications on August 22nd, 2024
Patent Applications by General Electric Company on August 22nd, 2024
General Electric Company: 20 patent applications
General Electric Company has applied for patents in the areas of F02C7/36 (4), F01D1/26 (4), F02C3/06 (4), F02K3/06 (4), F02K3/077 (4) F02C7/36 (4), F23R3/06 (2), C04B37/003 (1), C04B41/009 (1), F01D5/147 (1)
With keywords such as: turbine, engine, section, component, area, ceramic, resonant, fan, layer, and assembly in patent application abstracts.
Patent Applications by General Electric Company
Inventor(s): Jerome Geoffrey Magnant of Rexford NY (US) for general electric company, Jared Hogg Weaver of Clifton Park MN (US) for general electric company
IPC Code(s): C04B37/00
CPC Code(s): C04B37/003
Abstract: a unitary ceramic component is provided that includes a first ceramic component; a second ceramic component; and a series-hybrid joint coupling the first ceramic component to the second ceramic component. the series-hybrid joint includes a first bonding interface coupling the first ceramic component and the second ceramic component and a second bonding interface coupling the first ceramic component and the second ceramic component. the first bonding interface exhibits properties that are different from the second bonding interface.
Inventor(s): Joseph John Shiang of Niskayuna NY (US) for general electric company, Jared Hogg Weaver of Clifton Park NY (US) for general electric company, Jerome Geoffrey Magnant of Rexford NY (US) for general electric company, Daniel Gene Dunn of Guilderland NY (US) for general electric company
IPC Code(s): C04B41/00, C04B41/50, C04B41/52, C04B41/89
CPC Code(s): C04B41/009
Abstract: methods for joining a first ceramic component to a second ceramic component to form a unitary ceramic component are provided. the method includes positioning a bonding sheet between a first ceramic component and a second ceramic component. the bonding sheet defines a plurality of voids. the method also includes densifying the bonding sheet with an infiltrate composition at a densification temperature to form a bonding interface comprising a ceramic material that forms a bonding interface between the first ceramic component to the second ceramic component into a unitary ceramic component.
20240280024. TURBINE ENGINE WITH COMPOSITE AIRFOILS_simplified_abstract_(general electric company)
Inventor(s): Nicholas Joseph Kray of Mason OH (US) for general electric company, Arthur William Sibbach of Boxford MA (US) for general electric company
IPC Code(s): F01D5/14, F01D5/28
CPC Code(s): F01D5/147
Abstract: a turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. the turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. an airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
Inventor(s): Arthur William Sibbach of Boxford MA (US) for general electric company, Nicholas Joseph Kray of Mason OH (US) for general electric company, Gregory Carl Gemeinhardt of Park Hills KY (US) for general electric company
IPC Code(s): F01D5/28, F02C3/04
CPC Code(s): F01D5/28
Abstract: a turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. the turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. the airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
Inventor(s): Nicholas Joseph Kray of Mason OH (US) for general electric company, Arthur William Sibbach of Boxford MA (US) for general electric company
IPC Code(s): F01D5/28, F01D5/14
CPC Code(s): F01D5/282
Abstract: a gas turbine engine includes a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. sets of blades can be rotatably driven about the longitudinal axis in the compressor section and the turbine section, with adjacent vanes provided between sets of blades. the airfoil structure defining one or more of the blades or vanes can include a core structure which includes a woven or foam core, with an exterior woven layer.
Inventor(s): Clive Andrew Morgan of Laurens SC (US) for general electric company, Zachary Allen Hase of Miamisburg OH (US) for general electric company, Brian Lee DeVilbiss of West Chester OH (US) for general electric company, Daniel Endecott Osgood of Loveland OH (US) for general electric company
IPC Code(s): F01D5/30, F02C3/04
CPC Code(s): F01D5/3007
Abstract: a turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. a set of blades are circumferentially arranged in the turbine section and the compressor section. a set of dovetails mounts the set of blades to a disk, rotated about the engine centerline. each dovetail can include a set of lobes defining complementary recesses, collectively defining a neck for mounting to the disk.
20240280033. INSERTION TOOL AND METHOD_simplified_abstract_(general electric company)
Inventor(s): Julian Matthew Foxall of Bristol (GB) for general electric company, Trevor Owen Hawke of Bristol (GB) for general electric company, Andrew Crispin Graham of Badminton (GB) for general electric company, Chiara Mellucci of Bristol (GB) for general electric company, Todd William Danko of Niskayuna NY (US) for general electric company, Ambarish Jayant Kulkarni of Glenville NY (US) for general electric company, Michael Dean Fullington of West Chester OH (US) for general electric company, Margeaux Wallace of Niskayuna NY (US) for general electric company
IPC Code(s): F01D21/00, F01D25/28
CPC Code(s): F01D21/003
Abstract: an insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. the insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.
20240280049. GAS TURBINE ENGINE_simplified_abstract_(general electric company)
Inventor(s): Daniel Alan Niergarth of Norwood OH (US) for general electric company, Jorge de Luis of Cincinnati OH (US) for general electric company, Douglas Downey Turner of West Chester OH (US) for general electric company, Michael Macrorie of Winchester MA (US) for general electric company, Keith W. Wilkinson of Portsmouth NH (US) for general electric company, Arthur William Sibbach of Boxford MA (US) for general electric company, Vincenzo Martina of Turin (IT) for general electric company
IPC Code(s): F02C6/06, F02C7/18
CPC Code(s): F02C6/06
Abstract: a gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (a) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (a) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (egt) in degrees celsius, a maximum drive turbine shaft torque (t) in newton meters, and a corrected specific power (csp) in newtons squared times degrees celsius over meters squared, wherein the corrected specific power is determined as follows:
20240280049. GAS TURBINE ENGINE_simplified_abstract_(general electric company)
Inventor(s): Daniel Alan Niergarth of Norwood OH (US) for general electric company, Jorge de Luis of Cincinnati OH (US) for general electric company, Douglas Downey Turner of West Chester OH (US) for general electric company, Michael Macrorie of Winchester MA (US) for general electric company, Keith W. Wilkinson of Portsmouth NH (US) for general electric company, Arthur William Sibbach of Boxford MA (US) for general electric company, Vincenzo Martina of Turin (IT) for general electric company
IPC Code(s): F02C6/06, F02C7/18
CPC Code(s): F02C6/06
Abstract:
20240280049. GAS TURBINE ENGINE_simplified_abstract_(general electric company)
Inventor(s): Daniel Alan Niergarth of Norwood OH (US) for general electric company, Jorge de Luis of Cincinnati OH (US) for general electric company, Douglas Downey Turner of West Chester OH (US) for general electric company, Michael Macrorie of Winchester MA (US) for general electric company, Keith W. Wilkinson of Portsmouth NH (US) for general electric company, Arthur William Sibbach of Boxford MA (US) for general electric company, Vincenzo Martina of Turin (IT) for general electric company
IPC Code(s): F02C6/06, F02C7/18
CPC Code(s): F02C6/06
Abstract: wherein csp is greater than 0.0001194�egt−0.103�egt+22.14 and less than 0.0003294�egt−0.306�egt+77.91; and wherein egt is greater than 525 degrees celsius and less than 1250 degrees celsius.
Inventor(s): William Joseph Bowden of Cleves OH (US) for general electric company, Steven B. Morris of Mason OH (US) for general electric company, Vicente Jerez Fidalgo of South Bend IN (US) for general electric company
IPC Code(s): F02C7/042, F01D25/02, F01D25/12
CPC Code(s): F02C7/042
Abstract: an engine includes a fan section having an open fan defining an axial centerline and a rotor. the rotor includes a plurality of fan blades mounted to a hub and being rotatable about the axial centerline. the engine also includes a turbomachine downstream of the fan section. the turbomachine includes a core cowl that defines an engine inlet and encloses turbomachinery. further, the engine includes an airflow diverting assembly downstream of the fan section and upstream of the engine inlet. the airflow diverting assembly includes at least one fluid passageway formed into at least a portion of the hub for diverting at least a portion of a boundary layer on a surface of the hub away from the surface of the hub to reduce distortion caused by the boundary layer in the turbomachinery.
Inventor(s): Joshua Tyler Mook of Cincinnati OH (US) for general electric company, John Alan Manteiga of Lynn MA (US) for general electric company, Christopher Williams of Hamilton OH (US) for general electric company
IPC Code(s): F02C7/06, F01D25/16, F01D25/24, F02C3/14, F02C7/18, F02C7/20, F04D29/053, F04D29/056, F04D29/32, F04D29/54
CPC Code(s): F02C7/06
Abstract: the present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. an integral superstructure supports the rotating component. the superstructure includes a bearing portion that contacts the shaft. a stator portion, is spaced a critical dimension radially outward, from the rotor. a first annular transfer portion extends axially forward from the bearing to the stator portion. a second annular transfer portion extends axially aft from the stator portion to a mounting flange. the mounting flange connects the superstructure to a frame. the superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. the rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.
Inventor(s): Arthur William Sibbach of Boxford MA (US) for general electric company, Adam Tomasz Pazinski of Warsaw (PL) for general electric company
IPC Code(s): F02C7/18, F01D17/12, F02C7/04
CPC Code(s): F02C7/18
Abstract: an aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
20240280054. THERMAL INSULATION ASSEMBLY_simplified_abstract_(general electric company)
Inventor(s): Karthick Gourishankar of Bangalore (IN) for general electric company, Mohandas Nayak of Bangalore (IN) for general electric company, Rejin Ratnakar of Bangalore (IN) for general electric company, Eric Daniel Holbrook of Vandalia OH (US) for general electric company
IPC Code(s): F02C7/24, B32B1/08, B32B3/28, B32B9/00, B32B9/04
CPC Code(s): F02C7/24
Abstract: a thermal insulation assembly for a duct through which high temperature fluid, greater than 500 fahrenheit, passes. the thermal insulation assembly can experience pressures less than 80 kilopascals and can be included in a turbine engine. the thermal insulation assembly includes a first foil layer confronting the duct, a second foil layer spaced from the first foil layer, an insulation layer between the first foil layer and the second foil layer, an opacifier layer provided on the insulation layer, and a reflective layer applied to the opacifier layer.
Inventor(s): Pranav R. Kamat of Bengaluru (IN) for general electric company, Bhaskar Nanda Mondal of Bengaluru (IN) for general electric company, Jeffrey D. Clements of Evendale OH (US) for general electric company
IPC Code(s): F02C7/36, F01D1/26, F02C3/06, F02K3/06, F02K3/077
CPC Code(s): F02C7/36
Abstract: a turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. the fan assembly includes a plurality of fan blades. the low-pressure turbine includes 3-5 rotating stages. the low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. in some instances, the area ratio is within a range of 3.1-5.1.
Inventor(s): Pranav R. Kamat of Bengaluru (IN) for general electric company, Bhaskar Nanda Mondal of Bengaluru (IN) for general electric company, Jeffrey D. Clements of Evendale OH (US) for general electric company
IPC Code(s): F02C7/36, F01D1/26, F02C3/06, F02K3/06, F02K3/077
CPC Code(s): F02C7/36
Abstract: a turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. the fan assembly includes a plurality of fan blades. the low-pressure turbine includes 3-5 rotating stages. the low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. in some instances, the area ratio is within a range of 3.1-5.1.
Inventor(s): Pranav R. Kamat of Bengaluru (IN) for general electric company, Bhaskar Nanda Mondal of Bengaluru (IN) for general electric company, Jeffrey D. Clements of Evendale OH (US) for general electric company
IPC Code(s): F02C7/36, F01D1/26, F02C3/06, F02K3/06, F02K3/077
CPC Code(s): F02C7/36
Abstract: a turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. the fan assembly includes a plurality of fan blades. the low-pressure turbine includes 3-5 rotating stages. the low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. in some instances, the area ratio is within a range of 3.1-5.1.
Inventor(s): Pranav R. Kamat of Bengaluru (IN) for general electric company, Bhaskar Nanda Mondal of Bengaluru (IN) for general electric company, Jeffrey D. Clements of Evendale OH (US) for general electric company
IPC Code(s): F02C7/36, F01D1/26, F02C3/06, F02K3/06, F02K3/077
CPC Code(s): F02C7/36
Abstract: a turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. the fan assembly includes a plurality of fan blades. the low-pressure turbine includes 3-5 rotating stages. the low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. in some instances, the area ratio is within a range of 3.1-5.1.
Inventor(s): Wendy Wenling Lin of Montgomery OH (US) for general electric company, David Herman of Beavercreek OH (US) for general electric company, Trevor Howard Wood of Clifton Park NY (US) for general electric company, Nikolai N. Pastouchenko of Latham NY (US) for general electric company, Kishore Ramakrishnan of Rexford NY (US) for general electric company, Timothy Richard DePuy of Liberty Township OH (US) for general electric company, Robert William Davidoff of Carnegie PA (US) for general electric company
IPC Code(s): F02K1/82, B33Y80/00, F03D80/00, G10K11/16, G10K11/172
CPC Code(s): F02K1/827
Abstract: an acoustic core may include an array of resonant cells configured as a plurality of resonant cell groups. the resonant cell groups may include a plurality of resonant cells configured as a partitioned resonant cell that include a converging resonant cell and a diverging resonant cell. the converging resonant cell and the diverging resonant cell may be defined by a plurality of cell walls integrally formed with one another and a partition integrally formed with the plurality of cell walls. the partition may at least partially delimit the converging resonant cell from the diverging resonant cell. the converging resonant cell may define an upper resonant space delimited by the partition and a top face of the array of resonant cells. the diverging resonant cell may define a lower resonant space delimited by the partition and a bottom face of the array of resonant cells.
Inventor(s): Bhavya Naidu Panduri of Bengaluru (IN) for general electric company, Perumallu Vukanti of Bengaluru (IN) for general electric company, Pradeep Naik of Bengaluru (IN) for general electric company, Michael T. Bucaro of Arvada CO (US) for general electric company, Sibtosh Pal of Mason OH (US) for general electric company, Aritra Chakraborty of Bengaluru (IN) for general electric company, Pabitra Badhuk of Bengaluru (IN) for general electric company, Arijit Sinha Roy of Bengaluru (IN) for general electric company, Ajoy Patra of Bengaluru (IN) for general electric company, R Narasimha Chiranthan of Bengaluru (IN) for general electric company
IPC Code(s): F23R3/00
CPC Code(s): F23R3/06
Abstract: a combustor for a gas turbine engine. the combustor having a dome wall, a set of fuel cups, an inner liner, an outer liner, and a set of dilution passages. the dome wall, the inner liner, and the outer liner, together, at least partially defining a combustion chamber. the set of dilution passages terminating in a plurality of dilution holes arranged in a dilution hole arrangement provided in at least one of the inner liner or the outer liner. the dilution hole arrangement having at least a first subset of dilution holes arranged along a first leg and a second subset of dilution holes arranged along a second leg.
20240280265. COMBUSTOR FUEL NOZZLE ASSEMBLY_simplified_abstract_(general electric company)
Inventor(s): Nayan Vinod Patel of Liberty Township OH (US) for general electric company, Michael A. Benjamin of Cincinnati OH (US) for general electric company
IPC Code(s): F23R3/34, F02C7/22, F23R3/06, F23R3/14, F23R3/28, F23R3/36
CPC Code(s): F23R3/06
Abstract: a turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. a combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. the fuel nozzle assembly can include an air flow passage and a fuel flow passage.
Inventor(s): Dustin F. Howard of Brookhaven GA (US) for general electric company
IPC Code(s): H02J3/24, G05B19/042, H02M5/42, H02P9/02
CPC Code(s): H02J3/24
Abstract: a method for decoupling a mechanical drivetrain resonance mode of an inverter-based resource from the external electrical system includes receiving one or more voltage feedback signals at a node between the inverter-based resource and the external electrical system. the method also includes filtering the one or more voltage feedback signals to extract changes in a voltage at a frequency associated with the drivetrain resonance mode. further, the method includes determining at least one current command or power command based on the filtered one or more voltage feedback signals. moreover, the method includes controlling the power converter according to the at least one current command and controlling the energy buffer according to the power command so as to reduce or eliminate the changes in the voltage at the frequency associated with the drivetrain resonance mode.
General Electric Company patent applications on August 22nd, 2024
- General Electric Company
- C04B37/00
- CPC C04B37/003
- General electric company
- C04B41/00
- C04B41/50
- C04B41/52
- C04B41/89
- CPC C04B41/009
- F01D5/14
- F01D5/28
- CPC F01D5/147
- F02C3/04
- CPC F01D5/28
- CPC F01D5/282
- F01D5/30
- CPC F01D5/3007
- F01D21/00
- F01D25/28
- CPC F01D21/003
- F02C6/06
- F02C7/18
- CPC F02C6/06
- F02C7/042
- F01D25/02
- F01D25/12
- CPC F02C7/042
- F02C7/06
- F01D25/16
- F01D25/24
- F02C3/14
- F02C7/20
- F04D29/053
- F04D29/056
- F04D29/32
- F04D29/54
- CPC F02C7/06
- F01D17/12
- F02C7/04
- CPC F02C7/18
- F02C7/24
- B32B1/08
- B32B3/28
- B32B9/00
- B32B9/04
- CPC F02C7/24
- F02C7/36
- F01D1/26
- F02C3/06
- F02K3/06
- F02K3/077
- CPC F02C7/36
- F02K1/82
- B33Y80/00
- F03D80/00
- G10K11/16
- G10K11/172
- CPC F02K1/827
- F23R3/00
- CPC F23R3/06
- F23R3/34
- F02C7/22
- F23R3/06
- F23R3/14
- F23R3/28
- F23R3/36
- H02J3/24
- G05B19/042
- H02M5/42
- H02P9/02
- CPC H02J3/24
