Patents by Inventor Richard Freer

Richard Freer 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: 10998806
    Abstract: An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.
    Type: Grant
    Filed: December 7, 2018
    Date of Patent: May 4, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Latulipe, Richard Freer
  • Patent number: 10865761
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: December 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Patent number: 10826415
    Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.
    Type: Grant
    Filed: May 14, 2019
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Latulipe, Richard Freer
  • Publication number: 20200186017
    Abstract: An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.
    Type: Application
    Filed: December 7, 2018
    Publication date: June 11, 2020
    Inventors: Eric LATULIPE, Richard FREER
  • Publication number: 20200186016
    Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.
    Type: Application
    Filed: December 7, 2018
    Publication date: June 11, 2020
    Inventors: Eric LATULIPE, Richard FREER
  • Publication number: 20200186018
    Abstract: An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.
    Type: Application
    Filed: December 7, 2018
    Publication date: June 11, 2020
    Inventors: Eric LATULIPE, Richard FREER
  • Publication number: 20200080484
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080486
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a sleeve extending at least partially axially along the heater rod, the sleeve having an inner surface facing and spaced apart from the rod, the inner surface defining a pocket adjacent to the heater rod and having a radial depth relative to the axis.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080482
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080530
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Publication number: 20200080488
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis to a rod end distal from the base, the glow plug heater rod sized such that that the rod end is exposed to a combustion chamber of the gas turbine engine when the base is connected to the casing.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080489
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the heater rod extending from the base along an axis and terminating in a rod end, a peripheral wall extending circumferentially around the rod end and having a distal end directed away from the base, a gap between the peripheral wall and the heater rod, the rod end being axially retracted relative the distal end of the peripheral wall.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200083791
    Abstract: A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.
    Type: Application
    Filed: May 14, 2019
    Publication date: March 12, 2020
    Inventors: Eric LATULIPE, Richard FREER
  • Publication number: 20200080492
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the igniter having a ventilation path extending from an inlet to an outlet, the inlet fluidly connectable to a spacing located between a casing and a combustor liner of the gas turbine engine, the outlet extending circumferentially around the glow plug heater rod and oriented axially relative to the axis, the outlet fluidly connectable to a combustion chamber of the gas turbine engine delimited by the combustor liner.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080491
    Abstract: There is disclosed a method of servicing a gas turbine engine having a spark plug igniter connected to a spark plug igniter socket of the engine, the method including: removing the spark plug from the spark plug igniter socket of the gas turbine engine; inserting a glow plug igniter having a base configured for matingly engaging the spark plug igniter socket; and securing the glow plug igniter to the gas turbine engine.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080490
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080483
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a plurality of fins disposed circumferentially around the glow plug heater rod, the fins extending axially along at least a portion of the glow plug heater rod. A gas turbine engine including such an igniter is further disclosed.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200079521
    Abstract: There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.
    Type: Application
    Filed: May 14, 2019
    Publication date: March 12, 2020
    Inventors: Eric LATULIPE, Richard Freer
  • Publication number: 20200083823
    Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.
    Type: Application
    Filed: May 14, 2019
    Publication date: March 12, 2020
    Inventors: Eric LATULIPE, Richard FREER
  • Publication number: 20200079518
    Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.
    Type: Application
    Filed: May 14, 2019
    Publication date: March 12, 2020
    Inventors: Eric Latulipe, Richard Freer