General Electric Company patent applications on September 26th, 2024
Patent Applications by General Electric Company on September 26th, 2024
General Electric Company: 26 patent applications
General Electric Company has applied for patents in the areas of F01D11/02 (3), F01D11/08 (3), F01D11/00 (2), F02C7/22 (2), F23R3/28 (2) F02C7/22 (2), F23R3/06 (2), F01D11/001 (2), F01D11/025 (2), F01D11/08 (2)
With keywords such as: seal, turbine, engine, assembly, rotor, between, fan, segment, flow, and comprising in patent application abstracts.
Patent Applications by General Electric Company
Inventor(s): Christopher James Hayden of Delanson NY (US) for general electric company, Victor Petrovich Ostroverkhov of Ballstone Lake NY (US) for general electric company, William Thomas Carter, Jr. of Galway NY (US) for general electric company
IPC Code(s): B22F12/70, B22F10/28, B22F12/37, B33Y30/00
CPC Code(s): B22F12/70
Abstract: an additive manufacturing (am) apparatus is provided, having a build unit including a powder delivery mechanism, a powder recoating mechanism, and an irradiation beam directing mechanism. the am apparatus further includes a build platform and a fluid flow mechanism that includes an inlet body forming an inlet plenum and a collector body extended from the inlet body. the collector body forms a collector plenum in fluid communication with the inlet plenum. the collector body forms an outlet opening, wherein the outlet opening is positioned proximate to the an inner portion of the build platform. the outlet opening is configured to provide a flow of fluid toward an outer portion of the build platform.
Inventor(s): Joshua Tyler Mook of Loveland OH (US) for general electric company, William Joseph Steele of Lawrenceburg IN (US) for general electric company, Mary Kathryn Thompson of Fairfield Township OH (US) for general electric company, David Scott Simmermon of Felicity OH (US) for general electric company, Michael Thomas Gansler of Mason OH (US) for general electric company
IPC Code(s): B23K26/064, B22F10/20, B22F10/28, B22F10/36, B22F10/366, B22F12/44, B23K26/06, B23K26/067, B23K26/073, B23K26/342, B29C64/153, B33Y30/00, G02B3/00, G02B26/08
CPC Code(s): B23K26/064
Abstract: an irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. the micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. the focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.
Inventor(s): Keith Edward James Blodgett of Milford OH (US) for general electric company, William J. Bowden of Cleves OH (US) for general electric company, Egbert Geertsema of Cincinnati OH (US) for general electric company
IPC Code(s): B64D27/14, B64C1/26, B64D27/40, B64D29/06, B64D35/02
CPC Code(s): B64D27/14
Abstract: an aircraft comprising a fuselage and an unducted turbine engine. the fuselage having a divot with an upstream edge and a downstream edge. the divot is defined by a straight reference line having a length (l) and a maximum depth (h) relative to the straight reference line. the unducted turbine engine having an engine core, a nacelle, and a set of blades. a first flow ratio (fr1) is equal to: h/l.
Inventor(s): Christopher Michael Puleo of Niskayuna NY (US) for general electric company, Erik Leeming Kvam of Niskayuna NY (US) for general electric company, Pak Kin Wong of State College PA (US) for general electric company, Peter Torab of Edinboro PA (US) for general electric company, Christine Lynne Surrette of Albany NY (US) for general electric company
IPC Code(s): C12Q1/24, C12Q1/18, G01N33/49
CPC Code(s): C12Q1/24
Abstract: the subject matter of the present disclosure generally relates to techniques for isolating bacterial cells from a biological sample comprising red blood cells. using an aggregating agent and an anticoagulant during sedimentation permits separation of bacterial pathogens in the sample from red blood cells. the separated sedimentation layer, which is enriched in any bacterial pathogens, can be centrifuged and resuspended to concentrate the bacteria for additional analysis, such as bacterial identification and/or antibiotic susceptibility tests.
Inventor(s): Sreekar Karnati of Guilderland NY (US) for general electric company, Martin Matthew Morra of Glenville NY (US) for general electric company
IPC Code(s): C23F15/00
CPC Code(s): C23F15/00
Abstract: a protected component is provided, which includes: a substrate defining a surface; and a regenerative surface treatment on the surface of the substrate. the substrate comprises an aluminum-based alloy. the regenerative surface treatment comprises an array of environmentally reactive deposits dispersed on the surface of the substrate, with each environmentally reactive deposit of the array defining a discrete region on the surface. the array of environmentally reactive deposits comprise at least one reactive element comprising al, zn, v, ce, dy, er, eu, gd, ho, la, lu, nd, pr, sc, sm, tb, tm, y, yb, mo, si, ca, w, a mixture thereof, or alloys thereof.
20240318556. SHAFT FOR A TURBOMACHINE_simplified_abstract_(general electric company)
Inventor(s): Prateek Jalan of Bengaluru (IN) for general electric company, Kudum Shinde of Bengaluru (IN) for general electric company, Milind Dhabade of Bengaluru (IN) for general electric company, Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, Tyler F. Hooper of Lynn MA (US) for general electric company
IPC Code(s): F01D5/02
CPC Code(s): F01D5/027
Abstract: a turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. the shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. the at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.
Inventor(s): Vidyashankar Ramasastry Buravalla of Bangalore (IN) for general electric company
IPC Code(s): F01D5/14, F02C7/00
CPC Code(s): F01D5/147
Abstract: a gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine centerline. an airfoil is located in one of the fan section, the compressor section, or the turbine section. the airfoil defines an interior and extends between a leading edge and a trailing edge defining a chord-wise direction, and extending between a root and a tip defining a span-wise direction. at least one stiffener is located within the interior, having a deformation threshold, and including at least one crush initiator formed on the at least one stiffener. the crush initiator determines deformation geometry of the at least one stiffener in response to a force acting on the at least one stiffener exceeding the deformation threshold.
Inventor(s): Grant Robert Portune of Cincinnati OH (US) for general electric company, Steven Douglas Johnson of Milford OH (US) for general electric company, Mallikarjun Metri of Bengaluru (IN) for general electric company, Ajith Jogi of Bengaluru (IN) for general electric company, Pratish Patil of Bengaluru (IN) for general electric company, Nageswar Rao Ganji of Bengaluru (IN) for general electric company, Rahul Anil Bidkar of Clifton Park NY (US) for general electric company, Prateek Jalan of Bengaluru (IN) for general electric company, Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, David Raju Yamarthi of Bengaluru (IN) for general electric company, Narendra Anand Hardikar of Bengaluru (IN) for general electric company, Chandrashekhar Kandukuri of Bengaluru (IN) for general electric company
IPC Code(s): F01D11/00, F16J15/16
CPC Code(s): F01D11/001
Abstract: a turbine engine is provided. the gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.
Inventor(s): Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, Chandrashekhar Kandukuri of Bengaluru (IN) for general electric company, David Raju Yamarthi of Bengaluru (IN) for general electric company, Rajesh Kumar of Bengaluru (IN) for general electric company, Tajinder Singh of Bengaluru (IN) for general electric company
IPC Code(s): F01D11/00, F01D11/02
CPC Code(s): F01D11/001
Abstract: a turbine engine is provided. the gas turbine engine includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments supported at least in part by the carrier, the plurality of seal segments having a first seal segment and a second seal segment, the first and second seal segments each having a seal face forming a fluid bearing with the rotor; and a seal support assembly comprising a tangential spring extension extending between the first seal segment and the second seal segment for biasing the first seal segment away from the second seal segment in the circumferential direction.
Inventor(s): Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, David Raju Yamarthi of Bengaluru (IN) for general electric company, Chandrashekhar Kandukuri of Bengaluru (IN) for general electric company, Deepak Trivedi of Halfmoon NY (US) for general electric company, Narendra Anand Hardikar of Bengaluru (IN) for general electric company, Vidyashankar Ramasastry Buravalla of Bengaluru (IN) for general electric company, Steven Douglas Johnson of Milford OH (US) for general electric company, Amit Goyal of Bengaluru (IN) for general electric company, Grant Robert Portune of Cincinnati OH (US) for general electric company, Himanshu Gupta of Bengaluru (IN) for general electric company, Srinivasan Swaminathan of Bengaluru (IN) for general electric company, Shalini Thimmegowda of Bengaluru (IN) for general electric company, Guru Venkata Dattu Jonnalagadda of Ponnur (IN) for general electric company, Shalabh Saxena of Bengaluru (IN) for general electric company, Prateek Jalan of Bengaluru (IN) for general electric company
IPC Code(s): F01D11/02
CPC Code(s): F01D11/025
Abstract: a turbine engine is provided. the turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.
Inventor(s): Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, David Raju Yamarthi of Bengaluru (IN) for general electric company, Narendra Anand Hardikar of Bengaluru (IN) for general electric company
IPC Code(s): F01D11/02, F01D11/08, F16J15/44
CPC Code(s): F01D11/025
Abstract: a turbine engine is provided. the gas turbine engine defines a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment having a seal face forming a fluid bearing with the rotor; and a seal support assembly comprising a torsional spring extension extending from the carrier, from the seal segment, or both, to bias the seal segment along the radial direction.
Inventor(s): Narendra Anand Hardikar of Hamilton OH (US) for general electric company, David Raju Yamarthi of Bengaluru (IN) for general electric company, Rahul Anil Bidkar of Clifton Park NY (US) for general electric company, Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, Prateek Jalan of Bengaluru (IN) for general electric company, Deepak Trivedi of Halfmoon NY (US) for general electric company
IPC Code(s): F01D11/08
CPC Code(s): F01D11/08
Abstract: a turbine engine is provided. the turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a first seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprising a prestressed spring assembly extending from the seal segment for biasing the seal segment along the radial direction.
Inventor(s): Sajinu Nangariyil of Bengaluru (IN) for general electric company, Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, Abhilash Pillai of Bengaluru (IN) for general electric company, Adam Tomasz Pazinski of Warsaw (PL) for general electric company, David Raju Yamarthi of Bengaluru (IN) for general electric company
IPC Code(s): F01D11/08
CPC Code(s): F01D11/08
Abstract: a turbine engine is provided. the gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly including a magnet assembly having a magnet coupled to the carrier or the seal segment for biasing the first seal segment along the radial direction.
Inventor(s): Dariusz Olczak of Warsaw (PL) for general electric company polska sp. z o.o.
IPC Code(s): F02C7/04, F02K3/00
CPC Code(s): F01D25/02
Abstract: a compressor comprises a rotor shaft including a forward end portion. the forward end portion defines an outer surface. a first row of compressor rotor blades is coupled to the rotor shaft downstream from the forward end portion. an outer casing at least partially surrounds the first row of compressor rotor blades and the outer surface of the forward end portion of the rotor shaft. the outer casing at least partially defines an inlet to the compressor. an inlet guide vane comprises a mounting portion, a tip portion, a leading-edge portion, and a trailing-edge portion. the mounting portion is coupled to the outer casing upstream from the first row of compressor rotor blades. the tip portion extends towards the outer surface of the forward end portion of the rotor shaft. a radial gap is defined between the tip portion and the outer surface.
Inventor(s): Michael A. Benjamin of Cincinnati OH (US) for general electric company, Manampathy G. Giridharan of Mason OH (US) for general electric company
IPC Code(s): F02C7/22, F23R3/28
CPC Code(s): F02C7/22
Abstract: a gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. the combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. the combustion chamber can be characterized by a combustor size rating between one inch and seven inches. in more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kn and sixty kn, in which the combustor size rating is a function of the core air flow parameter.
Inventor(s): Michael A. Benjamin of Cincinnati OH (US) for general electric company, Manampathy G. Giridharan of Mason OH (US) for general electric company
IPC Code(s): F02C7/22, F23R3/28
CPC Code(s): F02C7/22
Abstract: a gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. the combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. the combustion chamber can be characterized by a combustor size rating between one inch and seven inches. in more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kn and sixty kn, in which the combustor size rating is a function of the core air flow parameter.
20240318613. GAS TURBINE ENGINE WITH THIRD STREAM_simplified_abstract_(general electric company)
Inventor(s): Brandon Wayne Miller of Middletown OH (US) for general electric company, Randy M. Vondrell of Newport KY (US) for general electric company, David Marion Ostdiek of Liberty Township OH (US) for general electric company, Craig Williams Higgins of Liberty Township OH (US) for general electric company, Alexander Kimberley Simpson of Cincinnati OH (US) for general electric company, Syed Arif Khalid of West Chester OH (US) for general electric company, Jeffrey S. Spruill of Hillsboro OH (US) for general electric company, Daniel Lawrence Tweedt of West Chester OH (US) for general electric company, William Joseph Solomon of Montgomery OH (US) for general electric company, Kevin Edward Hinderliter of Cincinnati OH (US) for general electric company
IPC Code(s): F02K3/065, F02C3/06
CPC Code(s): F02K3/065
Abstract: a gas turbine engine is provided. the gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. the gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
Inventor(s): Bhaskar Nanda Mondal of Bengaluru (IN) for general electric company, Narayanan Payyoor of Bengaluru (IN) for general electric company, Pranav Kamat of Bengaluru (IN) for general electric company
IPC Code(s): F02K3/075, F02C3/06, F02K3/06
CPC Code(s): F02K3/075
Abstract: a turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine. the engine core has a length (l), and the high-pressure compressor has an exit stage diameter (d). a high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine. the high-pressure shaft is characterized by a high-speed shaft rating (hsr) from 1.5 to 6.2, and a ratio of l/dis from 2.1 to 4.3.
20240318660. TURBOMACHINE AND METHOD OF ASSEMBLY_simplified_abstract_(general electric company)
Inventor(s): Jixian Yao of Niskayuna NY (US) for general electric company, Trevor Howard Wood of Clifton Park NY (US) for general electric company, Kishore Ramakrishnan of Rexford NY (US) for general electric company, William Joseph Solomon of Montgomery OH (US) for general electric company, Giridhar Jothiprasad of Clifton Park NY (US) for general electric company, Aaron J. King of West Harrison OH (US) for general electric company
IPC Code(s): F04D29/38, F04D19/00
CPC Code(s): F04D29/384
Abstract: a turbomachine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, and an airfoil. the fan includes fan blades that extend radially outwardly toward the annular casing. the airfoil includes a first side and a second side coupled together at a leading edge and a trailing edge, a plurality of first chord sections defining at least one first chord length, and a plurality of second chord sections defining at least one second chord length. the plurality of first chord sections and second chord sections define a waveform along a leading edge of the airfoil. the fan has an average chord fan width according to a first performance factor. the fan has a quantity of fan blades according to a second performance factor.
20240318661. TURBOMACHINE AND METHOD OF ASSEMBLY_simplified_abstract_(general electric company)
Inventor(s): Jixian Yao of Niskayuna NY (US) for general electric company, Trevor Howard Wood of Clifton Park NY (US) for general electric company, Kishore Ramakrishnan of Rexford NY (US) for general electric company, William Joseph Solomon of Montgomery OH (US) for general electric company, Giridhar Jothiprasad of Clifton Park NY (US) for general electric company, Aaron J. King of West Harrison OH (US) for general electric company
IPC Code(s): F04D29/38, F04D19/00
CPC Code(s): F04D29/384
Abstract: a gas turbine engine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, a core turbine engine drivingly coupled to the fan and comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, and a variable bleed assembly comprising a variable bleed duct extending between a vb inlet and a vb outlet. the fan includes fan blades that extend radially outwardly toward the annular casing. the fan has an average chord fan width according to a first performance factor. the fan has a quantity of fan blades according to a second performance factor.
20240318688. LUBRICANT DRAINING BEARING ASSEMBLIES_simplified_abstract_(general electric company)
Inventor(s): Pravin Ganpati Patil of Bengaluru (IN) for general electric company, Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, Santosh Kumar Potnuru of Bengaluru (IN) for general electric company, Santosh Kumar Prasad of Bengaluru (IN) for general electric company, Pradeep Hemant Sangli of Bengaluru (IN) for general electric company, Rajesh Kumar of Bengaluru (IN) for general electric company, Mark L. Hopper of West Chester OH (US) for general electric company
IPC Code(s): F16C33/46, F16C33/66
CPC Code(s): F16C33/46
Abstract: lubricant draining bearing assemblies are disclosed. an example apparatus includes a first race, a second race, roller bearings positioned between the first race and the second race, and a cage positioned around the roller bearings between the first race and the second race, the cage including a first radial surface, a second radial surface, and an axial surface, the first radial surface facing the first race, the second radial surface facing the second race, the axial surface facing away from the roller bearings, the cage including at least one conduit extending between the first radial surface and at least one of the second radial surface or the axial surface, the conduit defining a flow path for a fluid out of a cavity between the first race, the roller bearings, and the cage.
20240318821. COMBUSTOR WITH A DILUTION PASSAGE_simplified_abstract_(general electric company)
Inventor(s): Manampathy G. Giridharan of Evendale OH (US) for general electric company, Pradeep Naik of Bengalura (IN) for general electric company, Michael A. Benjamin of West Chester OH (US) for general electric company
IPC Code(s): F23R3/06
CPC Code(s): F23R3/06
Abstract: a combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and at least one dilution passage. the compressed air passageway being formed between the casing, the inner liner and the outer liner. the combustion chamber being at least partially defined by the inner liner and the outer liner. the at least one dilution passage extending through at least one of the inner liner or the outer liner. the at least one dilution passage extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.
Inventor(s): Perumallu Vukanti of Bengaluru (IN) for general electric company, Sibtosh Pal of Mason OH (US) for general electric company, Pradeep Naik of Bengaluru (IN) for general electric company, R Narasimha Chiranthan of Bengaluru (IN) for general electric company, Ajoy Patra of Bengaluru (IN) for general electric company, Michael T. Bucaro of Arvada CO (US) for general electric company, Aritra Chakraborty of Bengaluru (IN) for general electric company, Arijit Sinha Roy of Bengaluru (IN) for general electric company, Pabitra Badhuk of Bengaluru (IN) for general electric company, Bhavya Naidu Panduri of Bengaluru (IN) for general electric company
IPC Code(s): F23R3/06
CPC Code(s): F23R3/06
Abstract: a gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. the combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. a fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. a first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. the first and second flow paths intersect at an intersection point to form a sheet of air.
20240319491. ALTERABLE OPTICAL STRUCTURES_simplified_abstract_(general electric company)
Inventor(s): Dhanushkodi Durai Mariappan of Guiderland NY (US) for general electric company, Gregory Daniel Dreifus of Troy NY (US) for general electric company, Xiaopeng Li of Rexford NY (US) for general electric company, James William Bray of Niskayuna NY (US) for general electric company, Greg Alan Radighieri of Sunnyvale TX (US) for general electric company
IPC Code(s): G02B26/00, G02B1/00
CPC Code(s): G02B26/004
Abstract: described herein are alterable optical structures. also described herein are methods of altering same.
20240322638. HIGH HEAT TRANSFER CRYOGENIC BEARING_simplified_abstract_(general electric company)
Inventor(s): Ernst Wolfgang Stautner of Niskayuna NY (US) for general electric company, Constantinos Minas of Slingerlands NY (US) for general electric company
IPC Code(s): H02K5/173, F16C32/04, H02K9/20, H02K9/22, H02K55/04
CPC Code(s): H02K5/1737
Abstract: a superconducting motor including a rotor, a heat sink, and a bearing. the rotor includes a superconducting winding formed from a superconducting material. the heat sink is positioned within the superconducting motor to absorb heat produced by the superconducting motor. the bearing includes an inner race, an outer race, and a rolling element. the bearing rotatably supports the rotor and is thermally connected to each of the rotor and the heat sink to transfer heat from the rotor to the heat sink. the rolling element is formed from a material having, at 25 k, a thermal conductivity of 20 w/mk or more and an ultimate tensile strength of 650 mpa or more. the rolling element may be formed from a copper alloy.
Inventor(s): Sreedhar Desabhatla of Bavaria (DE) for general electric company, John Andrew Leonard of Roanoke VA (US) for general electric company
IPC Code(s): H02M5/45, H02M1/08, H02M5/451, H02P27/06
CPC Code(s): H02M5/4505
Abstract: a system, including: a plurality of load commutated inverters (lcis) connected in parallel, wherein each lci includes: a source bridge for converting an alternating current (ac) voltage to a direct current (dc) voltage, wherein the source bridge includes at least one current switching device; a load bridge for converting the dc voltage from the source bridge to a variable frequency ac voltage; and a dc link coupling the source bridge to the load bridge; wherein each lci includes a respective current regulator for controlling the at least one current switching device in the source bridge of the lci to generate a current in the dc link.
Inventor(s): Stephen Francis BUSH of Latham NY (US) for general electric company
IPC Code(s): H04L41/0894, H04L41/0895
CPC Code(s): H04L41/0894
Abstract: techniques for communication over a communication network may include determining a plurality of network slices based on a plurality of services supported by the communication network, wherein each of the plurality of network slices supports communication of data associated with at least one service. a plurality of data streams may be configured within the communication network. each data stream being configured in accordance with at least one of a plurality of time-sensitive network policies. a first data stream of the plurality of data streams corresponding to a first network slice of the plurality of network slices may be determined.
General Electric Company patent applications on September 26th, 2024
- General Electric Company
- B22F12/70
- B22F10/28
- B22F12/37
- B33Y30/00
- CPC B22F12/70
- General electric company
- B23K26/064
- B22F10/20
- B22F10/36
- B22F10/366
- B22F12/44
- B23K26/06
- B23K26/067
- B23K26/073
- B23K26/342
- B29C64/153
- G02B3/00
- G02B26/08
- CPC B23K26/064
- B64D27/14
- B64C1/26
- B64D27/40
- B64D29/06
- B64D35/02
- CPC B64D27/14
- C12Q1/24
- C12Q1/18
- G01N33/49
- CPC C12Q1/24
- C23F15/00
- CPC C23F15/00
- F01D5/02
- CPC F01D5/027
- F01D5/14
- F02C7/00
- CPC F01D5/147
- F01D11/00
- F16J15/16
- CPC F01D11/001
- F01D11/02
- CPC F01D11/025
- F01D11/08
- F16J15/44
- CPC F01D11/08
- F02C7/04
- F02K3/00
- CPC F01D25/02
- General electric company polska sp. z o.o.
- F02C7/22
- F23R3/28
- CPC F02C7/22
- F02K3/065
- F02C3/06
- CPC F02K3/065
- F02K3/075
- F02K3/06
- CPC F02K3/075
- F04D29/38
- F04D19/00
- CPC F04D29/384
- F16C33/46
- F16C33/66
- CPC F16C33/46
- F23R3/06
- CPC F23R3/06
- G02B26/00
- G02B1/00
- CPC G02B26/004
- H02K5/173
- F16C32/04
- H02K9/20
- H02K9/22
- H02K55/04
- CPC H02K5/1737
- H02M5/45
- H02M1/08
- H02M5/451
- H02P27/06
- CPC H02M5/4505
- H04L41/0894
- H04L41/0895
- CPC H04L41/0894
