Patents by Inventor Morgan O'Rorke

Morgan O'Rorke 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).

  • Patent number: 12234816
    Abstract: In accordance with at least one aspect of this disclosure, a variable displacement pump system can include, a variable displacement pump disposed in a main line and configured to supply pressure to receive a low pressure fluid and to output a high pressure fluid. The main line can connect a hydraulic fluid source to a plurality of system actuators, where the variable displacement pump is disposed in the main line between the hydraulic fluid source and the plurality of system actuators to pressurize the hydraulic fluid.
    Type: Grant
    Filed: October 22, 2021
    Date of Patent: February 25, 2025
    Assignees: Hamilton Sundstrand Corporation, HAMILTON SUNDSTRAND CORPORATION
    Inventors: Matej Rutar, Morgan O'Rorke, Ryan Shook, Ryan Susca
  • Patent number: 12228151
    Abstract: A method of controlling an actuator includes switching a primary solenoid valve to a first mode to fluidically connect a supply pressure source to a control chamber of a pilot valve. A fluid from the supply pressure source is directed through the primary solenoid valve to fill the control chamber of the pilot valve and put the pilot valve in a first position. The first position fluidically connects a second chamber of the actuator to a return pressure source. The actuator includes a cylinder between the first chamber and the second chamber and a rod attached to the cylinder. The fluid from the supply pressure source is directed into the first chamber of the actuator to move the cylinder and the rod in a first direction while the pilot valve is in the first position.
    Type: Grant
    Filed: October 13, 2021
    Date of Patent: February 18, 2025
    Assignee: hamilton sundstrand corporation
    Inventors: Ryan Susca, Morgan O'Rorke, Todd Haugsjaahabink
  • Patent number: 12203491
    Abstract: A hydraulic actuator system of an aircraft includes a hydraulic actuator having a housing with a piston having a piston shaft with a piston head attached thereto and arranged within the housing. The piston head divides in internal volume of the housing into an extend cavity and a retract cavity and the extend cavity is configured to be connected to low pressure fluid source. The system also includes a pressure selector unit fluidly connected to the retract cavity and configured to be connected to the low pressure fluid source and to a high pressure fluid source. The unit include three solenoids with the first and second connected in parallel to the fluid sources and the third solenoid having a third solenoid first input connected to the first solenoid output, a third solenoid second input connected to the second solenoid output, and a third solenoid output connected to the retract cavity.
    Type: Grant
    Filed: April 22, 2022
    Date of Patent: January 21, 2025
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Ryan Prescott Susca, Morgan O'Rorke, Steve Doerner
  • Patent number: 12146478
    Abstract: A fuel pump system includes a main fuel pump between a system fuel inlet and a system fuel outlet, a fuel flow path at least partially defined between the main fuel pump and the system fuel outlet, and a support fuel pump between the system fuel inlet and the system fuel outlet. The support fuel pump is sized to provide more flow to the system fuel outlet, when in an active state, than the main fuel pump. The system includes a valve assembly in fluid communication with the support fuel pump configured and adapted to connect the support fuel pump to the system fuel outlet, and a pressure regulating valve in fluid communication with the fuel flow path between the main fuel pump and the system fuel outlet. The system includes an EHSV in fluid communication with the fuel flow path between the PRV and the system fuel outlet.
    Type: Grant
    Filed: May 26, 2022
    Date of Patent: November 19, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Morgan O′Rorke, Ryan Susca, Ryan Shook
  • Patent number: 12145719
    Abstract: A hydraulic actuator system includes a hydraulic actuator having a housing with a piston having a piston shaft arranged within the housing. The housing is formed to have first, second and third regions, wherein the first region is between the second and third regions and has a larger major dimension than the second and third regions. The system also includes first, second, and third piston heads connected to the piston shaft with the first piston head being tween the second and third piston, wherein the first position head is within the first region and divides the first region into two volumes, the second piston head is in the second region and defines a first volume and the third piston head is in the third region and defines a fourth volume. The system also includes a mode selection device operably connected to the first, second, third and fourth volume.
    Type: Grant
    Filed: April 22, 2022
    Date of Patent: November 19, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Frank Perrelli, Morgan O'Rorke
  • Patent number: 12140079
    Abstract: A fluid delivery system can include a main pump disposed in a primary fluid line configured to receive a low pressure fluid on a low pressure side and output a high pressure fluid on a high pressure side to provide flow from the fluid source to a fluid destination via the primary fluid line. An interconnected valve system can be disposed in the primary fluid line configured to control flow through the primary fluid line.
    Type: Grant
    Filed: November 29, 2021
    Date of Patent: November 12, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Morgan O'Rorke, Ryan Susca, Todd Haugsjaahabink
  • Patent number: 12055099
    Abstract: A two stage fuel delivery system for an aircraft includes a first stage pump including an inlet connected to a source of fuel and an outlet connected to a combustor assembly, and a second stage pump including an inlet portion connected to the source of fuel and an outlet portion connected to the combustor assembly. A bypass valve is connected between the source of fuel, the inlet, and the inlet portion. The bypass valve selectively disconnects the second stage pump from the source of fuel. A metering valve is connected to the inlet and the inlet portion. The metering valve includes a metering valve inlet and a metering valve outlet. A pressure regulating valve is connected to the metering valve. A stage monitoring system is configured to detect a change in operation of the second stage and control the bypass valve.
    Type: Grant
    Filed: July 19, 2022
    Date of Patent: August 6, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Ryan Prescott Susca, Todd Haugsjaahabink, Naison E. Mastrocola, Adrian L. Stoicescu, Zachary Allen Ray LeDuc, Eric Briggs, Morgan O'Rorke
  • Patent number: 11994117
    Abstract: A variable positive displacement pump actuator system for a variable positive displacement pump can include a supply line configured to provide a supply pressure, a main pump line configured to provide a pump pressure greater than the supply pressure from the variable positive displacement pump, and at least one electro-hydraulic servo valve (EHSV) in fluid communication with the supply line and the main pump line to receive the supply pressure and the pump pressure. The at least one electro-hydraulic servo valve can be configured to output a first regulated pressure and a second regulated pressure.
    Type: Grant
    Filed: October 4, 2021
    Date of Patent: May 28, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Ryan Susca, Morgan O'Rorke, Ryan Shook, Matej Rutar
  • Patent number: 11898496
    Abstract: A fuel system of an aircraft engine, having: a boost pump having an input and an output; one or more selector valves; a first component pump having an input fluidly coupled to the output of the boost pump and an output of the first component pump is configured to direct fuel to a first component via the one or more selector valves; and a second component pump having an input that is selectively coupled to either the input or the output of the boost pump by the one or more selector valves, and an output of the second component pump is fluidly coupled to a second component and selectively coupled to the first component by the one or more selector valves.
    Type: Grant
    Filed: July 21, 2022
    Date of Patent: February 13, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Ryan Prescott Susca, Morgan O'Rorke, Adrian L. Stoicescu
  • Publication number: 20240026825
    Abstract: A two stage fuel delivery system for an aircraft includes a first stage pump including an inlet connected to a source of fuel and an outlet connected to a combustor assembly, and a second stage pump including an inlet portion connected to the source of fuel and an outlet portion connected to the combustor assembly. A bypass valve is connected between the source of fuel, the inlet, and the inlet portion. The bypass valve selectively disconnects the second stage pump from the source of fuel. A metering valve is connected to the inlet and the inlet portion. The metering valve includes a metering valve inlet and a metering valve outlet. A pressure regulating valve is connected to the metering valve. A stage monitoring system is configured to detect a change in operation of the second stage and control the bypass valve.
    Type: Application
    Filed: July 19, 2022
    Publication date: January 25, 2024
    Inventors: Ryan Prescott Susca, Todd Haugsjaahabink, Naison E. Mastrocola, Adrian L. Stoicescu, Zachary Allen Ray LeDuc, Eric Briggs, Morgan O'Rorke
  • Publication number: 20240026826
    Abstract: A fuel system of an aircraft engine, having: a boost pump having an input and an output; one or more selector valves; a first component pump having an input fluidly coupled to the output of the boost pump and an output of the first component pump is configured to direct fuel to a first component via the one or more selector valves; and a second component pump having an input that is selectively coupled to either the input or the output of the boost pump by the one or more selector valves, and an output of the second component pump is fluidly coupled to a second component and selectively coupled to the first component by the one or more selector valves.
    Type: Application
    Filed: July 21, 2022
    Publication date: January 25, 2024
    Inventors: Ryan Prescott Susca, Morgan O'Rorke, Adrian L. Stoicescu
  • Patent number: 11859551
    Abstract: A fuel system can include a selection and shutoff valve (SSOV) configured to allow a primary flow having a primary flow pressure to pass therethrough in a first state such that the primary flow can travel to an output line. The SSOV can also be configured to shut off the primary flow in a second state to prevent the primary flow from travelling to the output line. In the second state, the SSOV can be configured to allow a secondary flow from a secondary flow source to pass therethrough such that the secondary flow can travel to the output line.
    Type: Grant
    Filed: January 21, 2022
    Date of Patent: January 2, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Morgan O'Rorke, Todd Haugsjaahabink, Matej Rutar, Ryan Susca
  • Patent number: 11851163
    Abstract: Hydraulic actuator systems of aircraft are described. The hydraulic actuator systems include a hydraulic actuator having a housing and piston therein. The piston includes a piston head separating the housing into a retract cavity and an extend cavity. An actuator controller is hydraulically coupled to the retract cavity by a first hydraulic line and hydraulically coupled to the extend cavity by a second hydraulic line and configured to control a hydraulic pressure within each of the retract cavity and the extend cavity to control actuation of the hydraulic actuator. A position-lock controller is arranged along at least one of the first hydraulic line and the second hydraulic line, the position-lock controller is configured to hydraulically decouple the actuator controller from at least one of the retract cavity and the extend cavity.
    Type: Grant
    Filed: April 25, 2022
    Date of Patent: December 26, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Frank Perrelli, Morgan O'Rorke
  • Patent number: 11852172
    Abstract: A solenoid driven actuator system includes a first solenoid having at least one pressure input and a pressure outlet downstream from the at least one pressure input. The system includes a second solenoid having at least one pressure input and a pressure outlet downstream from the at least one pressure input. The system includes a pressure-switching valve operatively coupled to the first and second solenoids. The system includes an actuator operatively coupled to the pressure outlet of the second solenoid.
    Type: Grant
    Filed: February 18, 2022
    Date of Patent: December 26, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Morgan O'Rorke, Steve Doerner, Ryan Susca
  • Publication number: 20230383736
    Abstract: A fuel pump system includes a main fuel pump between a system fuel inlet and a system fuel outlet, a fuel flow path at least partially defined between the main fuel pump and the system fuel outlet, and a support fuel pump between the system fuel inlet and the system fuel outlet. The support fuel pump is sized to provide more flow to the system fuel outlet, when in an active state, than the main fuel pump. The system includes a valve assembly in fluid communication with the support fuel pump configured and adapted to connect the support fuel pump to the system fuel outlet, and a pressure regulating valve in fluid communication with the fuel flow path between the main fuel pump and the system fuel outlet. The system includes an EHSV in fluid communication with the fuel flow path between the PRV and the system fuel outlet.
    Type: Application
    Filed: May 26, 2022
    Publication date: November 30, 2023
    Inventors: Morgan O'Rorke, Ryan Susca, Ryan Shook
  • Publication number: 20230339603
    Abstract: Hydraulic actuator systems of aircraft are described. The hydraulic actuator systems include a hydraulic actuator having a housing and piston therein. The piston includes a piston head separating the housing into a retract cavity and an extend cavity. An actuator controller is hydraulically coupled to the retract cavity by a first hydraulic line and hydraulically coupled to the extend cavity by a second hydraulic line and configured to control a hydraulic pressure within each of the retract cavity and the extend cavity to control actuation of the hydraulic actuator. A position-lock controller is arranged along at least one of the first hydraulic line and the second hydraulic line, the position-lock controller is configured to hydraulically decouple the actuator controller from at least one of the retract cavity and the extend cavity.
    Type: Application
    Filed: April 25, 2022
    Publication date: October 26, 2023
    Inventors: Frank Perrelli, Morgan O'Rorke
  • Publication number: 20230339605
    Abstract: A hydraulic actuator system includes a hydraulic actuator having a housing with a piston having a piston shaft arranged within the housing. The housing is formed to have first, second and third regions, wherein the first region is between the second and third regions and has a larger major dimension than the second and third regions. The system also includes first, second, and third piston heads connected to the piston shaft with the first piston head being tween the second and third piston, wherein the first position head is within the first region and divides the first region into two volumes, the second piston head is in the second region and defines a first volume and the third piston head is in the third region and defines a fourth volume. The system also includes a mode selection device operably connected to the first, second, third and fourth volume.
    Type: Application
    Filed: April 22, 2022
    Publication date: October 26, 2023
    Inventors: Frank Perrelli, Morgan O'Rorke
  • Publication number: 20230339604
    Abstract: A hydraulic actuator system of an aircraft includes a hydraulic actuator having a housing with a piston having a piston shaft with a piston head attached thereto and arranged within the housing. The piston head divides in internal volume of the housing into an extend cavity and a retract cavity and the extend cavity is configured to be connected to low pressure fluid source. The system also includes a pressure selector unit fluidly connected to the retract cavity and configured to be connected to the low pressure fluid source and to a high pressure fluid source. The unit include three solenoids with the first and second connected in parallel to the fluid sources and the third solenoid having a third solenoid first input connected to the first solenoid output, a third solenoid second input connected to the second solenoid output, and a third solenoid output connected to the retract cavity.
    Type: Application
    Filed: April 22, 2022
    Publication date: October 26, 2023
    Inventors: Ryan Prescott Susca, Morgan O'Rorke, Steve Doerner
  • Patent number: 11746710
    Abstract: A fluid flow system includes a main valve having a spool, a first chamber, and a second chamber. A pressure difference between the first chamber and the second chamber is configured to move the spool to control fluid flow. An electromechanical meter interface device (EMID) is in fluid communication with at least one of the first and second chambers of the main valve. The EMID is configured to meter fluid from a first source and a second source to the at least one of the first chamber and the second chamber. The first source has a different pressure from the second source. A fixed orifice is arranged between the main valve and the EMID. A fuel system for a gas turbine engine is also disclosed.
    Type: Grant
    Filed: November 23, 2021
    Date of Patent: September 5, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Morgan O'Rorke, Ryan Susca, Todd Haugsjaahabink
  • Publication number: 20230265937
    Abstract: A solenoid driven actuator system includes a first solenoid having at least one pressure input and a pressure outlet downstream from the at least one pressure input. A second solenoid has at least one pressure input and a pressure outlet downstream from the at least one pressure input. A transfer solenoid operatively coupled to the first and second solenoids. An actuator valve operatively coupled to a pressure outlet of the transfer solenoid.
    Type: Application
    Filed: February 18, 2022
    Publication date: August 24, 2023
    Inventors: Morgan O'Rorke, Steve Doerner, Ryan Susca