Patents by Inventor Jeffrey Joseph White
Jeffrey Joseph White 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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Patent number: 10807723Abstract: An aircraft outflow valve with a heat exchanger is disclosed herein. The aircraft outflow valve can include a heat exchanger that includes an air flow path. Air can flow through the air flow path and exit the outflow valve through an opening at the end of the air flow path. Such airflow can regulate the internal pressure of the aircraft and can also dissipate heat from the outflow valve. The outflow valve can further include a liquid coolant flow path. The liquid coolant flow path can be coupled to liquid coolant lines of electronics of the aircraft. Thus, heat from the electronics of the aircraft can be dissipated through heat transfer between the coolant and the outflow valve, which is accordingly cooled by the airflow through the heat exchanger.Type: GrantFiled: November 2, 2018Date of Patent: October 20, 2020Assignee: THE BOEING COMPANYInventor: Jeffrey Joseph White
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Patent number: 10780850Abstract: Supplemental power systems for aircraft are described. One example is a power conversion system for an electrical power system in a twin engine aircraft having a first generator and a second generator is described. The power conversion system includes a first branch, a second branch, and a selector. The first branch has a first input, a first power converter, and a first output configured for coupling to an aircraft electrical distribution system. The second branch includes a second input, a second power converter, and a second output configured for coupling to the aircraft electrical distribution system. The selector is coupled between the first branch and the second branch. The selector is configured to selectively connect the first generator to the first branch or to the first and second branches. The selector is also configured to selectively connect the second generator to the second branch or the first and second branches.Type: GrantFiled: September 6, 2018Date of Patent: September 22, 2020Assignee: The Boeing CompanyInventors: Jeffrey Joseph White, Thomas F. Currier
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Publication number: 20200140094Abstract: An aircraft outflow valve with a heat exchanger is disclosed herein. The aircraft outflow valve can include a heat exchanger that includes an air flow path. Air can flow through the air flow path and exit the outflow valve through an opening at the end of the air flow path. Such airflow can regulate the internal pressure of the aircraft and can also dissipate heat from the outflow valve. The outflow valve can further include a liquid coolant flow path. The liquid coolant flow path can be coupled to liquid coolant lines of electronics of the aircraft. Thus, heat from the electronics of the aircraft can be dissipated through heat transfer between the coolant and the outflow valve, which is accordingly cooled by the airflow through the heat exchanger.Type: ApplicationFiled: November 2, 2018Publication date: May 7, 2020Inventor: Jeffrey Joseph White
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Publication number: 20190016280Abstract: Supplemental power systems for aircraft are described. One example is a power conversion system for an electrical power system in a twin engine aircraft having a first generator and a second generator is described. The power conversion system includes a first branch, a second branch, and a selector. The first branch has a first input, a first power converter, and a first output configured for coupling to an aircraft electrical distribution system. The second branch includes a second input, a second power converter, and a second output configured for coupling to the aircraft electrical distribution system. The selector is coupled between the first branch and the second branch. The selector is configured to selectively connect the first generator to the first branch or to the first and second branches. The selector is also configured to selectively connect the second generator to the second branch or the first and second branches.Type: ApplicationFiled: September 6, 2018Publication date: January 17, 2019Inventors: Jeffrey Joseph White, Thomas F. Currier
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Patent number: 10093250Abstract: Supplemental power systems for aircraft are described. One example is a power conversion system for an electrical power system in a twin engine aircraft having a first generator and a second generator is described. The power conversion system includes a first branch, a second branch, and a selector. The first branch has a first input, a first power converter, and a first output configured for coupling to an aircraft electrical distribution system. The second branch includes a second input, a second power converter, and a second output configured for coupling to the aircraft electrical distribution system. The selector is coupled between the first branch and the second branch. The selector is configured to selectively connect the first generator to the first branch or to the first and second branches. The selector is also configured to selectively connect the second generator to the second branch or the first and second branches.Type: GrantFiled: October 16, 2014Date of Patent: October 9, 2018Assignee: THE BOEING COMPANYInventors: Jeffrey Joseph White, Thomas F. Currier
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Patent number: 9646114Abstract: A method and apparatus for establishing a validated stable design for a stable electrical power system. An initial design for an electrical power system is established. The initial design for the electrical power system satisfies design requirements. The initial design for the electrical power system is simulated for a plurality of simulated operating conditions for the electrical power system to generate simulation data. Stability parameter requirements for a stable design for the electrical power system are established from the simulation data. A hardware implementation of the stable design for the electrical power system is tested to generate hardware testing data. The stable design for the electrical power system is validated using the hardware testing data to establish a validated stable design for the electrical power system.Type: GrantFiled: July 10, 2013Date of Patent: May 9, 2017Assignee: The Boeing CompanyInventors: Kamiar J. Karimi, Eugene V. Solodovnik, Zachary R. Lewis, Jeffrey Joseph White
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Publication number: 20160107588Abstract: Supplemental power systems for aircraft are described. One example is a power conversion system for an electrical power system in a twin engine aircraft having a first generator and a second generator is described. The power conversion system includes a first branch, a second branch, and a selector. The first branch has a first input, a first power converter, and a first output configured for coupling to an aircraft electrical distribution system. The second branch includes a second input, a second power converter, and a second output configured for coupling to the aircraft electrical distribution system. The selector is coupled between the first branch and the second branch. The selector is configured to selectively connect the first generator to the first branch or to the first and second branches. The selector is also configured to selectively connect the second generator to the second branch or the first and second branches.Type: ApplicationFiled: October 16, 2014Publication date: April 21, 2016Inventors: Jeffrey Joseph White, Thomas F. Currier
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Publication number: 20150019175Abstract: A method and apparatus for establishing a validated stable design for a stable electrical power system. An initial design for an electrical power system is established. The initial design for the electrical power system satisfies design requirements. The initial design for the electrical power system is simulated for a plurality of simulated operating conditions for the electrical power system to generate simulation data. Stability parameter requirements for a stable design for the electrical power system are established from the simulation data. A hardware implementation of the stable design for the electrical power system is tested to generate hardware testing data. The stable design for the electrical power system is validated using the hardware testing data to establish a validated stable design for the electrical power system.Type: ApplicationFiled: July 10, 2013Publication date: January 15, 2015Inventors: Kamiar J. Karimi, Eugene V. Solodovnik, Zachary R. Lewis, Jeffrey Joseph White
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Patent number: 8861147Abstract: A system and method for protecting a power system. A generator is tripped in response to identifying a current on the generator that is greater than a first current threshold for a first time delay. The generator is also tripped in response to identifying the current on the generator that is greater than a second current threshold for a second time delay. The first current threshold is larger than the second current threshold and the first time delay is shorter than the second time delay.Type: GrantFiled: April 25, 2012Date of Patent: October 14, 2014Assignee: The Boeing CompanyInventors: Jeffrey Joseph White, Evelyn M. Matheson, Kamiar J. Karimi
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Publication number: 20130286515Abstract: A system and method for protecting a power system. A generator is tripped in response to identifying a current on the generator that is greater than a first current threshold for a first time delay. The generator is also tripped in response to identifying the current on the generator that is greater than a second current threshold for a second time delay. The first current threshold is larger than the second current threshold and the first time delay is shorter than the second time delay.Type: ApplicationFiled: April 25, 2012Publication date: October 31, 2013Applicant: THE BOEING COMPANYInventors: Jeffrey Joseph White, Evelyn M. Matheson, Kamiar J. Karimi
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Patent number: 8125164Abstract: Apparatus, methods, and computer storage media provide for the establishment of a parallel motor controller architecture and the dynamic reconfiguration of the architecture to redirect power to various motors according to the changing power load requirements of the motors. According to embodiments described herein, the present power load requirement for each motor of a group of motors is determined. The number of motor controllers to connect to each motor to provide the present power load requirement is then determined. A power switching network that connects the motor controllers to the motors is configured to connect the determined number of motor controllers to the corresponding motors. As the power load requirements of the motors changes, the power switching network is dynamically reconfigured to redirect power accordingly.Type: GrantFiled: July 18, 2008Date of Patent: February 28, 2012Assignee: The Boeing CompanyInventor: Jeffrey Joseph White
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Publication number: 20100013419Abstract: Apparatus, methods, and computer storage media provide for the establishment of a parallel motor controller architecture and the dynamic reconfiguration of the architecture to redirect power to various motors according to the changing power load requirements of the motors. According to embodiments described herein, the present power load requirement for each motor of a group of motors is determined. The number of motor controllers to connect to each motor to provide the present power load requirement is then determined. A power switching network that connects the motor controllers to the motors is configured to connect the determined number of motor controllers to the corresponding motors. As the power load requirements of the motors changes, the power switching network is dynamically reconfigured to redirect power accordingly.Type: ApplicationFiled: July 18, 2008Publication date: January 21, 2010Inventor: Jeffrey Joseph White