View source for General Electric Company patent applications on July 25th, 2024

=Patent Applications by General Electric Company on July 25th, 2024=



[[:Category:General Electric Company|General Electric Company]]: 15 patent applications[[Category:General Electric Company]]

General Electric Company has applied for patents in the areas of [[:Category:F23R3/60|F23R3/60]] (3), [[:Category:F23R3/00|F23R3/00]] (2), [[:Category:G06F1/30|G06F1/30]] (1), [[:Category:F23R3/04|F23R3/04]] (1), [[:Category:F23R3/10|F23R3/10]] (1)
[[:Category:CPC_B64D37/34|B64D37/34]] (1), [[:Category:CPC_C09D11/322|C09D11/322]] (1), [[:Category:CPC_C22C27/02|C22C27/02]] (1), [[:Category:CPC_C23C28/042|C23C28/042]] (1), [[:Category:CPC_F01D5/186|F01D5/186]] (1)

With keywords such as: surface, fuel, about, between, atomic, percent, coating, component, cooling, and engine in patent application abstracts.




====Patent Applications by General Electric Company====


[[20240246693. FUEL COOLING SYSTEM_simplified_abstract_(general electric company)]]

Inventor(s): Brian Magann Rush of Niskayuna NY (US) for general electric company, Constantinos Minas of Slingerlands NY (US) for general electric company, William Morton of Schenectady NY (US) for general electric company

IPC Code(s): B64D37/34, F02C7/16, F02C7/22

CPC Code(s): B64D37/34




Abstract: a fuel system includes a fuel tank that stores fuel therein, and a fuel cooling system. the fuel cooling system includes a fuel cooling system fuel line in fluid communication with the fuel tank, one or more fuel cooling system heat exchangers in fluid communication with the fuel cooling system fuel line, and a fuel cooling system fuel pump. the fuel cooling system fuel pump pumps the fuel from the fuel tank such that the fuel flows through the fuel cooling system fuel line and into the one or more fuel cooling system heat exchangers to absorb heat from one or more aircraft components to become heated fuel. the heated fuel is returned and stored in the fuel tank.[[Category:B64D37/34]][[Category:F02C7/16]][[Category:F02C7/22]][[Category:CPC_B64D37/34]][[Category:general electric company]]



[[20240247162. Fabrication of Chromium Metal Mixtures in the Form of Core-Shell Nanoparticles_simplified_abstract_(general electric company)]]

Inventor(s): Louis Lefebvre of Valcourt  (CA) for general electric company, Ehsan Marzbanrad of Waterloo  (CA) for general electric company, Ehsan Toyserkani of Waterloo  (CA) for general electric company, Boxin Zhao of Waterloo  (CA) for general electric company, Jeremy Vandenberg of Brinston  (CA) for general electric company

IPC Code(s): C09D11/322, B22F1/054, B22F1/0545, B22F1/17, B22F9/24, B82Y30/00, B82Y40/00, C09D11/52

CPC Code(s): C09D11/322




Abstract: core-shell microparticles, along with methods of their fabrication and use, are provided. the core-shell microparticles may include a core comprising a first metallic material having a first chromium content, and a shell surrounding the core and comprising a second metallic material having a second chromium content, wherein the aerosol ink includes between 0.1% and 1% by weight of a radical scavenger and between 0.1% and 5% by weight of a dispersant.[[Category:C09D11/322]][[Category:B22F1/054]][[Category:B22F1/0545]][[Category:B22F1/17]][[Category:B22F9/24]][[Category:B82Y30/00]][[Category:B82Y40/00]][[Category:C09D11/52]][[Category:CPC_C09D11/322]][[Category:general electric company]]



[[20240247345. NIOBIUM-BASED ALLOY STRENGTHENED BY SILICIDE AND TURBINE HAVING TURBINE COMPONENT FORMED FROM_simplified_abstract_(general electric company)]]

Inventor(s): Akane Suzuki of Ballston Spa NY (US) for general electric company, Bernard Patrick Bewlay of Niskayuna NY (US) for general electric company, Chen Shen of Schenectady NY (US) for general electric company, Scott Michael Oppenheimer of Niskayuna NY (US) for general electric company, Patrick Thomas Brennan of Niskayuna NY (US) for general electric company

IPC Code(s): C22C27/02, C22C32/00

CPC Code(s): C22C27/02




Abstract: a niobium-silicide based alloy and a turbine having at least a turbine component formed from the niobium-silicide based alloy are provided. the niobium-silicide based alloy comprises: between about 14 atomic percent and about 24 atomic percent titanium (ti); between about 11 atomic percent and about 19 atomic percent silicon (si); between about 4 atomic percent and about 8 atomic percent chromium (cr); between about 2 atomic percent and about 6 atomic percent hafnium (hf); up to about 4 atomic percent aluminum (al); between about 0.5 atomic percent and about 1 atomic percent tin (sn); between about 5 atomic percent and about 15 atomic percent tantalum (ta); between about 1 atomic percent and about 5 atomic percent tungsten (w); up to about 5 atomic percent rhenium (re); up to about 5 atomic percent zirconium (zr); up to about 6 atomic percent yttrium (y); and a balance of niobium (nb).[[Category:C22C27/02]][[Category:C22C32/00]][[Category:CPC_C22C27/02]][[Category:general electric company]]



[[20240247378. COATING SYSTEMS INCLUDING INFILTRATION COATINGS AND REACTIVE PHASE SPRAY FORMULATION COATINGS_simplified_abstract_(general electric company)]]

Inventor(s): Hrishikesh Keshavan of Watervliet NY (US) for general electric company, Bernard Patrick Bewlay of Niskayuna NY (US) for general electric company, Jose Sanchez of Niskayuna NY (US) for general electric company, Margeaux Wallace of Niskayuna NY (US) for general electric company, Byron Pritchard of Cincinnati OH (US) for general electric company, Ambarish Kulkarni of Glenville NY (US) for general electric company

IPC Code(s): C23C28/04, C23C18/12, F01D5/28

CPC Code(s): C23C28/042




Abstract: a coating system configured to be applied to a thermal barrier coating of an article includes an infiltration coating configured to be applied to the thermal barrier coating. the infiltration coating infiltrates at least some pores of the thermal barrier coating. the infiltration coating decomposes within at least some pores of the thermal barrier coating to coat a portion of the at least some pores of the thermal barrier coating. the infiltration coating reduces a porosity of the thermal barrier coating. the coating system also includes a reactive phase spray formulation coat configured to be applied to the thermal barrier coating. the reactive phase spray formulation coating reacts with dust deposits on the thermal barrier coating[[Category:C23C28/04]][[Category:C23C18/12]][[Category:F01D5/28]][[Category:CPC_C23C28/042]][[Category:general electric company]]



[[20240247590. COMPONENT FOR A TURBINE ENGINE WITH A COOLING HOLE_simplified_abstract_(general electric company)]]

Inventor(s): Zachary Daniel Webster of Mason OH (US) for general electric company, Aaron Ezekiel Smith of Hermosa Beach CA (US) for general electric company, Gregory Terrence Garay of West Chester OH (US) for general electric company, Kirk D. Gallier of Cincinnati OH (US) for general electric company

IPC Code(s): F01D5/18, F01D9/02, F01D9/06

CPC Code(s): F01D5/186




Abstract: a component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. the connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. a metering section distance is measured between the centerline and a metering section wall of the metering section.[[Category:F01D5/18]][[Category:F01D9/02]][[Category:F01D9/06]][[Category:CPC_F01D5/186]][[Category:general electric company]]



[[20240247595. SEALING SYSTEM INCLUDING A SEAL ASSEMBLY BETWEEN COMPONENTS_simplified_abstract_(general electric company)]]

Inventor(s): Nicholas R. Overman of Sharonville OH (US) for general electric company

IPC Code(s): F01D11/00

CPC Code(s): F01D11/005




Abstract: a sealing system for sealing between components. the sealing system includes a first component, a second component, and a seal assembly including a seal member. the first component includes a first component surface, and the second component includes a second component surface. the second component surface is oriented in a direction transverse to the first contact surface. the seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. the first contact surface is configured to contact the first component surface and to slide relative to the first component surface. the second contact surface is configured to contact the second component surface and to slide relative to the second component surface. the second contact surface is oriented in a direction transverse to the first contact surface.[[Category:F01D11/00]][[Category:CPC_F01D11/005]][[Category:general electric company]]



[[20240247611. VARIABLE GEOMETRY INLET FOR TURBOPROPELLER INLET PRESSURE RECOVERY OPTIMIZATION_simplified_abstract_(general electric company)]]

Inventor(s): Trevor H. Wood of Clifton Park NY (US) for general electric company, Michael J. McMahon of Cincinnati OH (US) for general electric company

IPC Code(s): F02C7/042, F02C7/057

CPC Code(s): F02C7/042




Abstract: a turboprop engine includes a main nacelle body, a rotatable hub provided on the main nacelle body, a plurality of propellers connected to the rotatable hub, and a nacelle extension coupled to the main nacelle body, the nacelle extension including at least one wall defining an air intake inlet. the air intake inlet is movable in an airflow axis with respect to a trailing edge of a propeller in the plurality of propellers to vary a distance between the air intake inlet and the trailing edge of the propeller during various phases of operation of the turboprop engine.[[Category:F02C7/042]][[Category:F02C7/057]][[Category:CPC_F02C7/042]][[Category:general electric company]]



[[20240247614. TURBINE ENGINE WITH SHOCKWAVE ATTENUATION_simplified_abstract_(general electric company)]]

Inventor(s): Christopher Ryan Johnson of Fairfield OH (US) for general electric company, Paul Hadley Vitt of Liberty Twp OH (US) for general electric company, Eric Joseph Schroeder of Loveland OH (US) for general electric company, Carlos Gilberto Fernandez-Soto of Fairfield Twp OH (US) for general electric company

IPC Code(s): F02C7/24

CPC Code(s): F02C7/24




Abstract: a turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. a flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.[[Category:F02C7/24]][[Category:CPC_F02C7/24]][[Category:general electric company]]



[[20240247802. COMBUSTOR DEFLECTOR ASSEMBLY_simplified_abstract_(general electric company)]]

Inventor(s): Vijayaraj Sukumar 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, Ajoy Patra of Bengaluru  (IN) for general electric company, Karthikeyan Sampath of Bengaluru  (IN) for general electric company, Rimple Rangrej of Bengaluru  (IN) for general electric company, Hiranya Nath of Bengaluru  (IN) for general electric company, Krishnendu Chakraborty of Bengaluru  (IN) for general electric company, Narasimhan S. Sahana of Bengaluru  (IN) for general electric company, Saket Singh of Bengaluru  (IN) for general electric company, Ravindra Shankar Ganiger of Bengaluru  (IN) for general electric company

IPC Code(s): F23R3/00, F23R3/04, F23R3/10, F23R3/60

CPC Code(s): F23R3/002




Abstract: a deflector assembly for a combustor defining an operational fluid flow. the deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. one or more fastening mechanisms each extends through the deflector assembly. one or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. the one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.[[Category:F23R3/00]][[Category:F23R3/04]][[Category:F23R3/10]][[Category:F23R3/60]][[Category:CPC_F23R3/002]][[Category:general electric company]]



[[20240247803. DOME-DEFLECTOR ASSEMBLY FOR A COMBUSTOR OF A GAS TURBINE_simplified_abstract_(general electric company)]]

Inventor(s): Ravindra Shankar Ganiger of Bengaluru  (IN) for general electric company, Hiranya Nath of Bengaluru  (IN) for general electric company, Asim Ghosal of Bengaluru  (IN) for general electric company, Sripathi Mohan of Bengaluru  (IN) for general electric company, Nageswar Ganji of Bengaluru  (IN) for general electric company

IPC Code(s): F23R3/14, F23R3/00, F23R3/60

CPC Code(s): F23R3/14




Abstract: a dome-deflector assembly for a combustor of a gas turbine includes a dome portion having a dome-side swirler opening therethrough, and a deflector portion having a deflector-side swirler opening therethrough. the dome portion and the deflector portion are connected together to form a dome-deflector cavity therebetween. the deflector portion includes a first-side surface and a second-side surface, the second-side surface being arranged within the dome-deflector cavity, and the second-side surface including a plurality of stress-relief contours arranged in a pattern about the deflector-side swirler opening.[[Category:F23R3/14]][[Category:F23R3/00]][[Category:F23R3/60]][[Category:CPC_F23R3/14]][[Category:general electric company]]



[[20240247807. COMBUSTOR FOR A GAS TURBINE ENGINE_simplified_abstract_(general electric company)]]

Inventor(s): Karthikeyan Sampath of Bengaluru  (IN) for general electric company, Pradeep Naik of Bengaluru  (IN) for general electric company, Veeraraju Vanapalli of Bengaluru  (IN) for general electric company, Perumallu Vukanti of Bengaluru  (IN) for general electric company, Shai Birmaher of Cincinnati OH (US) for general electric company, Daniel J. Kirtley of Blue Ash OH (US) for general electric company, Deepak Ghiya of Bengaluru  (IN) for general electric company, Rample Rakeshkumar Rangrej of Bengaluru  (IN) for general electric company, Saket Singh of Bengaluru  (IN) for general electric company, Ravindra Shankar Ganiger of Bengaluru  (IN) for general electric company, Hiranya Kumar Nath of Bengaluru  (IN) for general electric company, Michael Anthony Benjamin of Cincinnati OH (US) for general electric company, Rajendra Mahadeorao Wankhade of Bengaluru  (IN) for general electric company

IPC Code(s): F23R3/60, B33Y80/00, F23R3/06

CPC Code(s): F23R3/60




Abstract: a combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.[[Category:F23R3/60]][[Category:B33Y80/00]][[Category:F23R3/06]][[Category:CPC_F23R3/60]][[Category:general electric company]]



[[20240247975. SHOCK WAVE DETECTION SYSTEMS AND METHODS_simplified_abstract_(general electric company)]]

Inventor(s): Daniel BIVOLARU of Hampton VA (US) for general electric company, Jiaji LIN of Flushing NY (US) for general electric company, George PAPADOPOULOS of Bohemia NY (US) for general electric company

IPC Code(s): G01H9/00, G02B6/12

CPC Code(s): G01H9/004




Abstract: a shock wave detection system includes an optical sensor configured to generate a sensor signal based on the received laser light, a processor, and a memory. the memory includes instructions stored thereon, which when executed by the processor cause the system to: generate a sensor signal based on the laser light; perform a digital fast fourier transform on the sensor signal; determine a power spectral density of the sensor signal based on the digital fast fourier transform; determine a difference in a frequency content before, during, and after a shock wave transition event based on the power spectral density; and determine a passing of the shock wave based on the difference in the frequency content.[[Category:G01H9/00]][[Category:G02B6/12]][[Category:CPC_G01H9/004]][[Category:general electric company]]



[[20240248522. REDUCED COMMON MODE VOLTAGE PULSE WIDTH MODULATION SWITCHING SCHEME WITH CAPACITOR VOLTAGE BALANCING FOR A MULTILEVEL POWER CONVERTER_simplified_abstract_(general electric company)]]

Inventor(s): Kum Kang Huh of Niskayuna NY (US) for general electric company, Hridya Ittamveettil of Bengaluru  (IN) for general electric company, Luis J. Garces of Niskayuna NY (US) for general electric company, Rajib Datta of Niskayuna NY (US) for general electric company, Di Pan of Schenectady NY (US) for general electric company, Yukai Wang of Schenectady NY (US) for general electric company

IPC Code(s): G06F1/30, B64D41/00, H02M1/00, H02M7/797

CPC Code(s): G06F1/30




Abstract: a multilevel power converter includes a plurality of switches, a first dc link capacitor, a second dc link capacitor, and one or more processors configured to: generate, for a duty cycle of the multilevel power converter, a pulse width modulated pulse pattern in accordance with a reduced common mode voltage scheme; modify the pulse width modulated pulse pattern to render a modified pulse pattern; and cause the plurality of switches to implement the duty cycle based at least in part on the modified pulse pattern to render a common mode voltage pulse to balance voltages at the first dc link capacitor and the second dc link capacitor.[[Category:G06F1/30]][[Category:B64D41/00]][[Category:H02M1/00]][[Category:H02M7/797]][[Category:CPC_G06F1/30]][[Category:general electric company]]



[[20240249521. SYSTEMS AND METHODS OF SERVICING EQUIPMENT_simplified_abstract_(general electric company)]]

Inventor(s): Andrew Crispin Graham of Badminton  (GB) for general electric company, David Scott Diwinsky of West Chester OH (US) for general electric company, Julian Matthew Foxall of Bristol  (GB) for general electric company

IPC Code(s): G06V20/20, G06V40/20, G08B7/06, G09B5/06, G09B19/00

CPC Code(s): G06V20/20




Abstract: systems and methods of servicing engines, an exemplary method of servicing an engine, the method including receiving, by one or more computing devices, information corresponding to one or more components of the engine; determining, by the one or more computing devices, a location of the one or more components of the engine with respect to a location of an augmented reality device; and presenting, in a current field of view display of the augmented reality device, at least a portion of the information corresponding to the one or more components of the engine, wherein the portion of the information includes a rendering of the one or more components, instructions regarding operations to be performed on the one or more components, directional arrows or contextual information associated with the one or more components, or any combination thereof.[[Category:G06V20/20]][[Category:G06V40/20]][[Category:G08B7/06]][[Category:G09B5/06]][[Category:G09B19/00]][[Category:CPC_G06V20/20]][[Category:general electric company]]



[[20240250530. SYSTEMS AND METHODS FOR REDUCING CARBON EMISSIONS FROM MACHINE LEARNING COMPUTATIONAL TASKS_simplified_abstract_(general electric company)]]

Inventor(s): Tapan Ravin Shah of Los Altos CA (US) for general electric company, Scott Charles Evans of Burnt Hills NY (US) for general electric company, Arunvenkataraman Subramanian of Dublin CA (US) for general electric company, Jeffrey Thomas Maskalunas of Schenectady NY (US) for general electric company, Sachini Piyoni Ekanayake Ekanayake Mudiyanselage of Troy NY (US) for general electric company

IPC Code(s): H02J3/00, H02J3/14

CPC Code(s): H02J3/004




Abstract: a computer system is provided. the computer system includes a scheduling computing device configured to receive computational task data defining a computational task to be performed, retrieve site data corresponding to each of a plurality of data processing computing devices, select, based on the computational task data and the site data, i) a first computational algorithm for executing the computational task, ii) a first data processing computing device of the plurality of data processing computing devices, and iii) at least one time period for executing the first computational algorithm by the first data processing computing device, wherein the first computational algorithm, the first data processing computing device, and the at least one time period are selected to facilitate reducing carbon dioxide emissions associated with executing the computational algorithm, and instruct the first data processing computing device to execute the first computational algorithm during the at least one time period.[[Category:H02J3/00]][[Category:H02J3/14]][[Category:CPC_H02J3/004]][[Category:general electric company]]



[[General Electric Company patent applications on July 25th, 2024]]



[[Category:General Electric Company]] [[Category:F23R3/60]] [[Category:F23R3/00]] [[Category:G06F1/30]] [[Category:F23R3/04]] [[Category:F23R3/10]]