General Electric Company patent applications on February 6th, 2025
Patent Applications by General Electric Company on February 6th, 2025
General Electric Company: 17 patent applications
General Electric Company has applied for patents in the areas of B64C11/48 (2), F02C7/06 (2), F01D9/04 (2), G06F30/23 (1), F02C7/14 (1) B64C11/48 (2), B25G1/06 (1), B64D27/12 (1), B64D45/00 (1), F01D9/041 (1)
With keywords such as: engine, pressure, having, turbine, flow, gas, configured, fan, component, and assembly in patent application abstracts.
Patent Applications by General Electric Company
20250042011. RIGIDIZABLE INSERTION TOOL_simplified_abstract_(general electric company)
Inventor(s): Chang Liu of Ho-Ho-Kus NJ (US) for general electric company, Grover Andrew Bennett, JR. of Esperance NY (US) for general electric company, Deepak Trivedi of Halfmoon NY (US) for general electric company, Andrew Crispin Graham of Badminton (GB) for general electric company
IPC Code(s): B25G1/06
CPC Code(s): B25G1/06
Abstract: a rigidizable insertion tool includes a first segment having a pin extension and a second segment having a pin slot that is elongated. the first segment and the second segment are connected via a joint comprising the pin extension of the first segment and the pin slot of the second segment. the pin extension is movable between a proximal end and a distal end of the pin slot with movement of the first segment relative to the second segment.
20250042537. AIRCRAFT WITH AN UNDUCTED FAN PROPULSOR_simplified_abstract_(general electric company)
Inventor(s): Sara Elizabeth Carle of Columbus OH (US) for general electric company, Daniel L. Tweedt of West Chester OH (US) for general electric company, Syed Arif Khalid of West Chester OH (US) for general electric company, Andrew Breeze-Stringfellow of Montgomery OH (US) for general electric company, William Bowden of Cleves OH (US) for general electric company
IPC Code(s): B64C11/48, F01D5/02
CPC Code(s): B64C11/48
Abstract: the present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. more specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. that higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.
20250042538. AIRCRAFT WITH AN UNDUCTED FAN PROPULSOR_simplified_abstract_(general electric company)
Inventor(s): Sara Elizabeth Carle of Columbus OH (US) for general electric company, Daniel L. Tweedt of West Chester OH (US) for general electric company, Syed Arif Khalid of West Chester OH (US) for general electric company, Andrew Breeze-Stringfellow of Montgomery OH (US) for general electric company, William Bowden of Cleves OH (US) for general electric company
IPC Code(s): B64C11/48, B64C3/14
CPC Code(s): B64C11/48
Abstract: the present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. more specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. that higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.
20250042558. AIRCRAFT WITH AN UNDUCTED FAN PROPULSOR_simplified_abstract_(general electric company)
Inventor(s): Sara Elizabeth Carle of Columbus OH (US) for general electric company, Daniel L. Tweedt of West Chester OH (US) for general electric company, Syed Arif Khalid of West Chester OH (US) for general electric company, Andrew Breeze-Stringfellow of Montgomery OH (US) for general electric company, William Bowden of Cleves OH (US) for general electric company
IPC Code(s): B64D27/12, B64C11/30
CPC Code(s): B64D27/12
Abstract: the present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. more specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. that higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.
20250042572. AIRCRAFT HEALTH STATUS PARAMETER DISPLAY_simplified_abstract_(general electric company)
Inventor(s): Michael C. SCHOLTEN of Grand Rapids MI (US) for general electric company, Richard J. Reiffer of Victor NY (US) for general electric company, Mark E. CRAFT of Eastleigh, Hampshire (GB) for general electric company, Omar HWAIL of Grand Rapids MI (US) for general electric company, Aram PENA MARTINEZ of Queretaro (MX) for general electric company
IPC Code(s): B64D45/00, G07C5/00
CPC Code(s): B64D45/00
Abstract: provided is a health management system (hms) for providing health status information about an aircraft to a user. the hms includes an aircraft health management unit (ahmu) on-board the aircraft configured for (i) monitoring the health status information when the aircraft is airborne or stationary and (ii) recording data representative of the monitored health status information and a ground-based data delivery system (dds) configured for (i) establishing an internet access portal for the ahmu to access webservice applications and (ii) facilitating communication between the dds and ahmu in accordance with protocols of the webservice applications. one of the webservice applications controls one session of the communication and another one of the webservice application controls another session of the communication and the recorded data is delivered to the dds during one of the sessions.
20250043688. VANE ASSEMBLY FOR OPEN FAN ENGINE_simplified_abstract_(general electric company)
Inventor(s): Sara Elizabeth Carle of Columbus OH (US) for general electric company, Daniel L. Tweedt of West Chester OH (US) for general electric company, Syed Arif Khalid of West Chester OH (US) for general electric company
IPC Code(s): F01D9/04
CPC Code(s): F01D9/041
Abstract: the present disclosure is generally related to a vane assembly for an open fan engine having a rotor and a stator. the vane assembly is a plurality of vanes each arranged about the stator. each of the vanes of the vane assembly has a leading edge (le) with a leading edge angle (lea). a combination of aircraft angle of attack, sideslip, and upwash due to lifting bodies can create a flow angularity into the engine. the leading edge angle (lea) of each of the vanes varies depending upon the circumferential location about the stator so that the impact on the flow angularity into the engine is reduced or increased in different circumferential regions.
Inventor(s): Timothy Leo Schelfaut of Lebanon OH (US) for general electric company
IPC Code(s): F01D11/20, F02C9/00
CPC Code(s): F01D11/20
Abstract: a method of operating a gas turbine engine includes operating the gas turbine engine in a first flight condition. the method further includes receiving a demand for a second flight condition that is different than the first flight condition. the method further includes determining a final target clearance and a transient target clearance between the first component and the second component. the final target clearance is associated with the second flight condition. the method further includes adjusting an engine acceleration rate to a nominal acceleration rate. the method further includes comparing an actual clearance with the transient target clearance after an increment of time. the method further includes adjusting the engine acceleration rate based on the comparison between the actual clearance and the transient target clearance, wherein the transient target clearance is adjusted at least partially based on the adjustment to the engine acceleration rate.
Inventor(s): David Yamarthi of Bengaluru (IN) for general electric company, Tod R. Steen of West Chester OH (US) for general electric company, Ravindra Shankar Ganiger of Bengaluru (IN) for general electric company, Kudum Shinde of Bengaluru (IN) for general electric company, Ankita Sinha of Bengaluru (IN) for general electric company, Aman Srivastava of Lucknow (IN) for general electric company, Narayanan Payyoor of Bengaluru (IN) for general electric company, Venkata Subramanya Sarma Devarakonda of Bengaluru (IN) for general electric company, Rajesh Kumar Undipalli of Bengaluru (IN) for general electric company, Dinesh Rakwal of Bengaluru (IN) for general electric company, Himanshu Gupta of Bengaluru (IN) for general electric company, Hrishi Ragesh of Trivandrum (IN) for general electric company
IPC Code(s): F01D21/00, F01D25/04, G01H3/00
CPC Code(s): F01D21/003
Abstract: a gas turbine engine includes a fan section having a plurality of fan blades, the fan section configured to generate an airflow through the gas turbine engine, an airflow passage having a core passage and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. the sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. the plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. a damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.
20250043697. LUBRICATION SYSTEM FOR A TURBINE ENGINE_simplified_abstract_(general electric company)
Inventor(s): Brandon W. Miller of Middletown OH (US) for general electric company, Arthur W. Sibbach of Boxford MA (US) for general electric company, Andrew Hudecki of Milford OH (US) for general electric company
IPC Code(s): F01D25/20, F02C7/06
CPC Code(s): F01D25/20
Abstract: a lubrication system for a turbine engine having a longitudinal centerline axis and one or more rotating components. the lubrication system includes a primary lubrication system that supplies lubricant to the one or more rotating components during normal operation of the turbine engine. the lubrication system also includes an auxiliary lubrication system. the auxiliary lubrication system includes an auxiliary reservoir and a lubricant dispersion device. the auxiliary reservoir stores the lubricant therein. the lubricant dispersion device rotates about the longitudinal centerline axis. the lubricant dispersion device collects the lubricant in the auxiliary reservoir and disperses the lubricant to the one or more rotating components as the lubricant dispersion device rotates.
Inventor(s): Kenneth R. Willett of Mukilteo WA (US) for general electric company
IPC Code(s): F01D25/24, F01D9/04
CPC Code(s): F01D25/243
Abstract: an apparatus for a turbine engine of a mating assembly with a casing and a shroud circumscribing the casing. one of the casing or shroud including at least one flange defining a v-groove. the other of the casing or shroud including an annular protrusion defining a v-blade received in the v-groove when the casing is mated with the shroud.
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): F02C6/20, F02C3/06, F02C7/06, F02C7/08, F02C7/36
CPC Code(s): F02C6/206
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.
Inventor(s): Scott Alan Schimmels of Miamisburg OH (US) for general electric company, Jeffrey Douglas Rambo of Mason OH (US) for general electric company, Timothy Richard DePuy of Liberty Township OH (US) for general electric company, Steven B. Morris of Mason OH (US) for general electric company, Eric Barre of Cincinnati OH (US) for general electric company, Brandon Wayne Miller of Middletown OH (US) for general electric company, Leonardo Aguilar Willys of Queretaro (MX) for general electric company, Victor Moreno Patan of Queretaro (MX) for general electric company
IPC Code(s): F02C7/045, F02C7/14, F02K3/04
CPC Code(s): F02C7/045
Abstract: a heat exchanger positioned within an annular duct of a gas turbine engine is provided. the heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. an effective transmission loss (etl) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. the heat exchanger includes a heat transfer section defining an acoustic length (l), and wherein an operational acoustic reduction ratio (oarr) is greater than or equal to 0.75 to achieve the etl at the operating condition.
Inventor(s): Kudum Shinde of Bengaluru (IN) for general electric company, Surender Reddy Bhavanam of Bengaluru (IN) for general electric company
IPC Code(s): F04D27/00, F02C7/057
CPC Code(s): F04D27/001
Abstract: a gas turbine engine including a frame, a plurality of fan blades configured to rotate about a longitudinal centerline axis of the gas turbine engine, and a mounting assembly coupling the frame to a structure. the gas turbine engine includes a sensor assembly coupled to the mounting assembly and having at least one sensor configured to detect a loading on the mounting assembly and to take a corrective action when propeller whirl is detected above a predetermined limit, and a feature configured to take a corrective action when propeller whirl is detected above a predetermined limit.
Inventor(s): Constantinos Minas of Slingerlands NY (US) for general electric company
IPC Code(s): F17C13/02, F17C13/04
CPC Code(s): F17C13/025
Abstract: methods and apparatus for pressure control systems in pressure vessels are disclosed herein. an example apparatus disclosed herein includes a cryogenic tank, a valve fluidly coupled to the cryogenic tank, machine readable instructions, and programmable circuitry to at least one of instantiate or execute the machine readable instructions to determine, based on a temperature of the cryogenic tank and a property of the cryogenic tank, a threshold pressure of the cryogenic tank, compare a pressure of the cryogenic tank to the threshold pressure, and after determining the pressure of the cryogenic tank does not satisfy the threshold pressure, actuate the valve until the pressure satisfies the threshold pressure.
Inventor(s): Brian S. McCarthy of Clifton Park NY (US) for general electric company, Justin John Gambone, JR. of Schenectady NY (US) for general electric company, Thomas C. Adcock of Glenville NY (US) for general electric company, Daniel J. Erno of Clifton Park NY (US) for general electric company, Christopher D. Immer of Niskayuna NY (US) for general electric company, Christina Vasil of Cohoes NY (US) for general electric company
IPC Code(s): G06F30/23, G06T17/20
CPC Code(s): G06F30/23
Abstract: a computer program product comprising a non-transitory computer-readable medium storing instructions, that when executed by a computer processor, cause the computer processor to perform obtain a model defining a geometry of a component for manufacturing using an additive manufacturing system, discretize the geometry of the component into a plurality of voxels, each voxel representing a volumetric portion of the component, identify voxels of the plurality of voxels having a value of stress greater than a threshold value, determine regions of the component contributing to the identified voxels having the value of stress greater than the threshold value through a build process simulation configured to iteratively simulate modifications to voxels of the component so that the value of stress of the identified voxels is reduced, modify the geometry of the regions of the component, and store an updated model of the component incorporating the modifications to the geometry.
20250047171. CONICAL MOTORS FOR USE WITH PUMPS_simplified_abstract_(general electric company)
Inventor(s): David Raju Yamarthi of Bangalore (IN) for general electric company, Ravindra Shankar Ganiger of Bangalore (IN) for general electric company, John R. Yagielski of Scotia NY (US) for general electric company, Venkata Subramanya Sarma Devarakonda of Bangalore (IN) for general electric company, Adam Joseph Wangler of West Chester OH (US) for general electric company, Brian G. Brzek of Clifton Park NY (US) for general electric company
IPC Code(s): H02K11/21, H02K7/00, H02K11/30
CPC Code(s): H02K11/21
Abstract: conical motors for use with pumps are disclosed. examples disclosed herein include an electric motor including a conical rotor, a first end of the conical rotor having a first diameter and a second end of the conical rotor having a second diameter, the second diameter different from the first diameter, and a conical stator aligned to the conical rotor.
Inventor(s): Brian Magann Rush of Niskayuna NY (US) for general electric company, William Dwight Gerstler of Niskayuna NY (US) for general electric company, Stefano Angelo Mario Lassini of Lowell MI (US) for general electric company, Todd Garrett Wetzel of Niskayuna NY (US) for general electric company
IPC Code(s): H05K7/20, B33Y80/00, F28D15/02, F28D15/04, G06F1/20
CPC Code(s): H05K7/20336
Abstract: according to one embodiment, a thermal management system for electronic devices, including a heat frame, a conformal slot portion, chassis frame, and heat fins wherein the heat frame, conformal slot, chassis frame, and heat fins are integrally formed as a unitary structure by additive manufacturing. in another example, there is a modular vapor assembly for electronic components having a vapor chamber comprising a component surface and a top surface with a vapor channel formed therebetween with at least one liquid receptacle and having a wick structure on at least some of an interior of the component surface. in operation, there is a circuit card with at least some of the electronic components coupled to the vapor chamber component surface and the wick structures transfer at least some of the liquid from the receptacle towards the electronic components, wherein the liquid turns to a vapor that moves towards the receptacle.
General Electric Company patent applications on February 6th, 2025
- General Electric Company
- B25G1/06
- CPC B25G1/06
- General electric company
- B64C11/48
- F01D5/02
- CPC B64C11/48
- B64C3/14
- B64D27/12
- B64C11/30
- CPC B64D27/12
- B64D45/00
- G07C5/00
- CPC B64D45/00
- F01D9/04
- CPC F01D9/041
- F01D11/20
- F02C9/00
- CPC F01D11/20
- F01D21/00
- F01D25/04
- G01H3/00
- CPC F01D21/003
- F01D25/20
- F02C7/06
- CPC F01D25/20
- F01D25/24
- CPC F01D25/243
- F02C6/20
- F02C3/06
- F02C7/08
- F02C7/36
- CPC F02C6/206
- F02C7/045
- F02C7/14
- F02K3/04
- CPC F02C7/045
- F04D27/00
- F02C7/057
- CPC F04D27/001
- F17C13/02
- F17C13/04
- CPC F17C13/025
- G06F30/23
- G06T17/20
- CPC G06F30/23
- H02K11/21
- H02K7/00
- H02K11/30
- CPC H02K11/21
- H05K7/20
- B33Y80/00
- F28D15/02
- F28D15/04
- G06F1/20
- CPC H05K7/20336
