Patents by Inventor Michael David Bailey
Michael David Bailey has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20240118451Abstract: A method can include receiving realizations of a model of a reservoir that includes at least one well where the realizations represent uncertainty in a multidimensional space; selecting a portion of the realizations in a reduced dimensional space to preserve an amount of the uncertainty; optimizing an objective function based at least in part on the selected portion of the realizations; outputting parameter values for the optimized objective function; and generating at least a portion of a field operations plan based at least in part on at least a portion of the parameter values.Type: ApplicationFiled: December 15, 2023Publication date: April 11, 2024Inventors: Vijaya Halabe, William J. Bailey, Michael David Prange, Trevor Graham Tonkin
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Patent number: 11933284Abstract: A vacuum exhaust system includes a plurality of turbo pumps that evacuate a plurality of vacuum chambers. A plurality of chamber valves are positioned between the turbo pumps and the plurality of vacuum chambers. A plurality of branch channels are each connected to a corresponding exhaust of the plurality of turbo pumps and a main channel is formed from a confluence of the branch channels. A booster vacuum pump is connected to the main channel. A backing vacuum pump is connected to an exhaust of the booster vacuum pump. A plurality of bypass channels, each having a valve, provide a fluid communication path between at least some of the plurality of vacuum chambers and the booster vacuum pump.Type: GrantFiled: November 27, 2019Date of Patent: March 19, 2024Assignee: Edwards LimitedInventors: Nigel Paul Schofield, Christopher Mark Bailey, Michael Andrew Galtry, Andrew David Mann
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Publication number: 20210309514Abstract: A solid state storage system includes a pressure-sealed storage unit defining an interior and having an outlet, an upper manifold and a lower manifold separated by a dividing plane having a set of ports, a set of chambers, and a solid state storage, wherein at least some gas is supplied to the outlet.Type: ApplicationFiled: June 21, 2021Publication date: October 7, 2021Inventors: Colin John HALSEY, Michael David BAILEY, Ross Jonathan WILLIAMS
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Patent number: 11040875Abstract: A hydrogen storage system includes a pressure-sealed storage unit defining an interior and having an outlet, an upper manifold and a lower manifold separated by a dividing plane having a set of ports, a set of chambers, and a hydrogen storage, wherein at least some hydrogen gas is supplied to the outlet.Type: GrantFiled: November 24, 2015Date of Patent: June 22, 2021Assignee: GE Aviation Systems LimitedInventors: Colin John Halsey, Michael David Bailey, Ross Jonathan Williams
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Patent number: 10926870Abstract: A method and apparatus for operating a power system architecture including an electrical power storage system, a power distribution bus selectively connected with the electrical power storage device, a hydraulic pump selectively connected with the electrical power storage device and a controller module communicatively connected with the electrical power storage system and the hydraulic pump.Type: GrantFiled: November 28, 2017Date of Patent: February 23, 2021Assignee: GE Aviation Systems LimitedInventors: Colin John Halsey, Michael David Bailey
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Patent number: 10913543Abstract: Systems and methods for providing power to one or more loads on an aircraft are provided. A power system for an aircraft can include a first fuel cell configured to provide base power to one or more loads on the aircraft. The power system can further include a second fuel cell configured to provide peak power to the one or more loads on the aircraft. The peak power can be a power exceeding the base power. The power system can further include an energy storage device configured to provide transient power to the one or more loads on the aircraft. The transient power can be a power exceeding the peak power. The power system can further include a controller configured to control delivery of power from the first fuel cell, the second fuel cell, and the energy storage device to the one or more loads on the aircraft.Type: GrantFiled: October 24, 2017Date of Patent: February 9, 2021Assignee: GE Aviation Systems LimitedInventors: Michael David Bailey, Colin John Halsey
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Patent number: 10814992Abstract: A power source for an aircraft including a solid oxide fuel cell and a proton exchange membrane fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell.Type: GrantFiled: November 16, 2017Date of Patent: October 27, 2020Assignee: GE Aviation Systems LimitedInventors: Colin John Halsey, Michael David Bailey
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Patent number: 10569904Abstract: In one aspect, there is disclosed a taxi vehicle comprising a chassis having a coupler to connect to a coupling location of a craft and a set of wheels with at least one electric motor coupled to the set of wheels. The taxi vehicle can include a fuel cell coupled to the at least one electric motor and a battery coupled to the fuel cell. The battery can be configured to supply peak power demand to the at least one electric motor to start moving the craft. The battery can receive charging from the fuel cell when not supplying peak power demand while the fuel cell supplies power to the at least one electric motor to continue moving the craft.Type: GrantFiled: November 7, 2017Date of Patent: February 25, 2020Assignee: GE Aviation Systems LimitedInventors: Colin John Halsey, Michael David Bailey
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Patent number: 10396565Abstract: A system for aircraft power distribution (100) includes a source of energy (112) to deliver an input power; a bus contactor (122); a set of switches (130) connected between the bus contactor and a set of essential and non-essential devices (132); a current analysis component (315) to determine a power level drawn from the source of current by the set of essential and non-essential devices (132); a variation reduction component (317) to determine an energization schedule of the set of essential and non-essential devices (132) based on reducing temporal variation in the input power drawn from the source of energy (112) to the bus contactor (122); and a switch control component (319) configured to adjust the set of switches (130) according to the energization schedule. If too much power is drawn, the set of switches (130) will be configured such as not to exceed the maximum power rating of the source (112).Type: GrantFiled: May 6, 2015Date of Patent: August 27, 2019Assignee: GE Aviation Systems LimitedInventors: Michael David Bailey, Colin John Halsey, Ross Jonathan Williams
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Publication number: 20180346330Abstract: A hydrogen storage system includes a pressure-sealed storage unit defining an interior and having an outlet, an upper manifold and a lower manifold separated by a dividing plane having a set of ports, a set of chambers, and a hydrogen storage, wherein at least some hydrogen gas is supplied to the outlet.Type: ApplicationFiled: November 24, 2015Publication date: December 6, 2018Inventors: Colin John HALSEY, Michael David BAILEY, Ross Jonathan WILLIAMS
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Publication number: 20180155044Abstract: A method and apparatus for operating a power system architecture including an electrical power storage system, a power distribution bus selectively connected with the electrical power storage device, a hydraulic pump selectively connected with the electrical power storage device and a controller module communicatively connected with the electrical power storage system and the hydraulic pump.Type: ApplicationFiled: November 28, 2017Publication date: June 7, 2018Inventors: Colin John Halsey, Michael David Bailey
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Publication number: 20180141674Abstract: Systems and methods for providing power to one or more loads on an aircraft are provided. A power system for an aircraft can include a first fuel cell configured to provide base power to one or more loads on the aircraft. The power system can further include a second fuel cell configured to provide peak power to the one or more loads on the aircraft. The peak power can be a power exceeding the base power. The power system can further include an energy storage device configured to provide transient power to the one or more loads on the aircraft. The transient power can be a power exceeding the peak power. The power system can further include a controller configured to control delivery of power from the first fuel cell, the second fuel cell, and the energy storage device to the one or more loads on the aircraft.Type: ApplicationFiled: October 24, 2017Publication date: May 24, 2018Inventors: Michael David BAILEY, Colin John HALSEY
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Publication number: 20180141675Abstract: An auxiliary power unit and a method for providing electricity to an aircraft with the auxiliary power unit where the auxiliary power unit includes a turbine with a compressor and an output shaft. A combustor coupled to the turbine and to a fuel source, and a solid oxide fuel cell coupled to the combustor, the compressor and to the fuel source.Type: ApplicationFiled: November 16, 2017Publication date: May 24, 2018Inventors: Colin John HALSEY, Michael David BAILEY
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Publication number: 20180134401Abstract: A power source for an aircraft including a solid oxide fuel cell and a solid oxide fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the solid oxide fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the solid oxide fuel cell.Type: ApplicationFiled: November 16, 2017Publication date: May 17, 2018Inventors: Colin John HALSEY, Michael David BAILEY
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Publication number: 20180138716Abstract: A system for aircraft power distribution (100) includes a source of energy (112) to deliver an input power; a bus contactor (122); a set of switches (130) connected between the bus contactor and a set of essential and non-essential devices (132); a current analysis component (315) to determine a power level drawn from the source of current by the set of essential and non-essential devices (132); a variation reduction component (317) to determine an energization schedule of the set of essential and non-essential devices (132) based on reducing temporal variation in the input power drawn from the source of energy (112) to the bus contactor (122); and a switch control component (319) configured to adjust the set of switches (130) according to the energization schedule. If too much power is drawn, the set of switches (130) will be configured such as not to exceed the maximum power rating of the source (112).Type: ApplicationFiled: May 6, 2015Publication date: May 17, 2018Inventors: Michael David BAILEY, Colin John HALSEY, Ross Jonathan WILLIAMS
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Publication number: 20180134413Abstract: In one aspect, there is disclosed a taxi vehicle comprising a chassis having a coupler to connect to a coupling location of a craft and a set of wheels with at least one electric motor coupled to the set of wheels. The taxi vehicle can include a fuel cell coupled to the at least one electric motor and a battery coupled to the fuel cell. The battery can be configured to supply peak power demand to the at least one electric motor to start moving the craft. The battery can receive charging from the fuel cell when not supplying peak power demand while the fuel cell supplies power to the at least one electric motor to continue moving the craft.Type: ApplicationFiled: November 7, 2017Publication date: May 17, 2018Inventors: Colin John HALSEY, Michael David BAILEY
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Patent number: 5850138Abstract: An electrical generator provides an output at a main stator winding which is excited by a main rotor winding. The main rotor winding is connected via a rectifier to a main exciter rotor winding which is excited by a main exciter field winding. A control circuit controls excitation of the main exciter field winding so as to stabilise the generator output voltage. The control circuit includes a detector for detecting excessive generator output voltage and a transistor switch for connecting a resistor in the current recirculation path of the main exciter field winding so as to prevent transient over-voltages caused by sudden load reductions.Type: GrantFiled: June 26, 1997Date of Patent: December 15, 1998Assignee: Lucas, Industries public limited companyInventors: Christopher John Adams, Michael David Bailey