Patents Assigned to Pratt & Whitney Canada Corp.
  • Patent number: 10995631
    Abstract: A gas turbine engine can have compressor or fan blades having elongated indentations formed in the radially-inner portion of the pressure face, each elongated indentation having a curved bottom extending transversally between sharp edges, the sharp edges delimiting a width of the elongated indentation from adjacent surfaces of the blade pressure face. During operation of the gas turbine engine, ice can accumulate on the blade, covering the elongated indentations, and the elongated indentations can cause crack appearance in the vicinity of its edge.
    Type: Grant
    Filed: April 1, 2019
    Date of Patent: May 4, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Alex Raykowski
  • Patent number: 10995660
    Abstract: A rotary engine casing having at least one end wall of an internal cavity for a rotor including a seal-engaging plate sealingly engaging the peripheral wall to partially seal the internal cavity and a member mounted adjacent the seal-engaging plate outside of the internal cavity. The member and seal-engaging plate having abutting mating surfaces which cooperate to define between them at least one fluid cavity communicating with a source of liquid coolant. When the casing includes a plurality of rotor housings, the end wall may be between rotor housings. A method of manufacturing a rotary engine casing is also discussed.
    Type: Grant
    Filed: October 9, 2019
    Date of Patent: May 4, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruno Villeneuve, Jean-Gabriel Gauvreau
  • Patent number: 10995675
    Abstract: A gas turbine engine with an accessory gearbox. The accessory gearbox is rotatably coupled to the engine drive shaft. The gearbox has a gear shaft rotatable about a gear shaft axis. The gear shaft has a first end drivingly engaged to a first accessory and a second end drivingly engaged to a second accessory.
    Type: Grant
    Filed: February 19, 2019
    Date of Patent: May 4, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michel Desjardins
  • 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: 10989409
    Abstract: A gas turbine engine combustor has a dome and a shell extending axially from the dome. The dome and the shell cooperates to define a combustion chamber. A dome heat shield is mounted to the dome inside the combustion chamber. A front heat shield is mounted to the shell inside the combustion chamber. The dome heat shield and the front heat shield have axially overlapping portions cooperating to define a flow guiding channel. The flow guiding channel has a length (L) and a height (h). The length (L) is at least equal to the height (h).
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: April 27, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Robert Sze
  • Patent number: 10989203
    Abstract: The shroud can have a wall curved radially outwardly from an axially oriented inlet to an outlet end, a structural member having a flange at the outlet end, and an insert of Greek Ascoloy exposed on an inner face of the wall.
    Type: Grant
    Filed: July 15, 2019
    Date of Patent: April 27, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Dave Menheere
  • Patent number: 10981675
    Abstract: The present disclosure provides methods and systems for propeller balancing of an aircraft comprising a propeller. Acceleration data is obtained from an acceleration sensor coupled to the aircraft. The acceleration data is filtered using a filter to obtain propeller-specific vibration data, the filter defining a range of acceptable frequencies associated with a frequency of rotation of the propeller. The propeller-specific vibration data is compared to trend data associated with the propeller. When the propeller-specific vibration data differs from the trend data beyond a predetermined threshold, an alert indicative of a balancing need for the propeller is issued.
    Type: Grant
    Filed: February 28, 2020
    Date of Patent: April 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Brian Wirth, Robert Winchcomb, Bruce Calvert, Robert Wigny
  • Patent number: 10982856
    Abstract: A fuel nozzle for injecting fuel and air into a combustor of a gas turbine engine, the fuel nozzle comprising: an outer component having an outward surface adapted for exposure to a flow of hot gas within the combustor, and an inward surface; an inner component concentrically disposed within the inward surface of outer component along a nozzle axis, the inner component defining an axially extending air flow channel; an air passage bore extending through the outward surface of the outer component and communicating with the air flow channel; and a thermal insulating sleeve disposed within the air passage bore, the sleeve having a sleeve body spaced apart from the outer component by an air gap.
    Type: Grant
    Filed: February 1, 2019
    Date of Patent: April 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Saeid Oskooei, Gavin Rohiteswar Kisun, Nadia Cheri Swaby, Roger Neil Antony Francis
  • Patent number: 10975707
    Abstract: A gas turbine engine rotary assembly comprises a disc mounted for rotation about an axis and having a first bayonet feature, a cover mounted to the disc; and a retaining ring having a second bayonet feature engaged with the first bayonet feature of the disc.
    Type: Grant
    Filed: December 19, 2018
    Date of Patent: April 13, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Vincent Paradis, Guy Lefebvre, John Pietrobon
  • Patent number: 10975740
    Abstract: An aircraft engine oil filler apparatus includes a filler tube configured to be received through a wall of an oil tank such that an open upper end of the filler tube is accessible from outside of the oil tank and a bottom end of the filler tube is disposed inside the oil tank, a valve received in the bottom end of the filler tube and movable between an open position in which the valve hydraulically connects the filler tube to the oil tank, and a closed position in which the valve hydraulically disconnects the filler tube from the oil tank, and a float disposed above the valve and operatively connected to the valve to move the valve from the open position to the closed position when oil inside the oil tank rises to a predetermined level. A method of operation of an oil filler apparatus is also described.
    Type: Grant
    Filed: July 2, 2019
    Date of Patent: April 13, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marion Daniel, Sean Powers, Rose Beaulieu
  • Patent number: 10975721
    Abstract: A case assembly for a turbine section has a structural outer case structurally connected to a gas generator upstream of the outer case and to an exhaust case downstream of the outer case. The assembly further comprises a containment ring mounted within the outer case and surrounding a plurality of axially spaced-apart turbine stages. An inner surface of the containment ring defines a plurality of shroud receiving portions. An annular plenum is defined between the outer case and the containment ring. The plenum has an inlet connected to a source of pressurized coolant. Outlets are circumferentially and axially distributed and defined through the containment ring. The outlets provides flow communication between the annular plenum and the plurality of axially spaced-apart turbine stages.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: April 13, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Remy Synnott
  • Patent number: 10975726
    Abstract: A sleeve is provided for supplying lubricant to an inter-shaft bearing mounted between co-axially mounted inner and outer shafts of a gas turbine engine. The sleeve has a sleeve annular outer surface and a sleeve annular inner surface. At least one lubricant supply connecting member extends from the sleeve outer surface for connection to a lubricant supply. At least one sleeve channel fluidly links the sleeve annular inner surface to the lubricant supply connecting member.
    Type: Grant
    Filed: January 15, 2019
    Date of Patent: April 13, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Ian A. MacFarlane
  • Patent number: 10975714
    Abstract: The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.
    Type: Grant
    Filed: November 22, 2018
    Date of Patent: April 13, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Lecuyer, Robert Huszar
  • Publication number: 20210101691
    Abstract: A hybrid electric propulsion (HEP) system can include a heat engine torque sensor connected between a heat engine and a combining gear box to sense a heat motor input torque input to the combining gear box, an electric motor torque sensor connected between an electric motor and the combining gear box to sense an electric motor input torque input to the combining gear box, and a combining gear box torque sensor connected to an output of the combining gearbox. The system can include a HEP controller operatively connected to each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor to receive one or more torque signals therefrom. The controller can be configured to output one or more output signals as a function of the signals from each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor.
    Type: Application
    Filed: August 24, 2020
    Publication date: April 8, 2021
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Michael Mark, Paul C. Imel, Leonid Guerchkovitch
  • Patent number: 10968820
    Abstract: A rotary engine includes an insert having a pilot subchamber defined therein and communicating with the internal cavity of the engine. A pilot fuel injector has a tip in communication with the pilot subchamber. An ignition element extends into an element cavity defined through the insert adjacent the pilot subchamber. The element cavity is in communication with the pilot subchamber through a communication opening defined in the insert between the element cavity and the pilot subchamber. The communication opening is smaller than a portion of the ignition element adjacent the communication opening such as to prevent the portion of the ignition element from completely passing through the communication opening upon breaking off of the portion of the ignition element from a remainder of the ignition element. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.
    Type: Grant
    Filed: September 18, 2019
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Gaul, Andre Julien, Bruno Villeneuve
  • Patent number: 10968827
    Abstract: A fan nose cone is disclosed for impeding icing and recovering momentum in a gas turbine engine. The fan nose cone comprises: an axially symmetric shell having a convex external surface and an internal surface, the shell having an opening in a forward end of the shell for communication with a source of heated pressurized air; and an axially symmetric deflector disposed forward of the opening, the deflector being configured to direct heated pressurized air exiting from the opening radially outwardly to flow in a downstream direction over the convex external surface of the shell during operation. The shell of the fan nose cone may have a rearward circumferential vent in communication with the source of heated pressurized air for directing heated pressurized from the vent in a radially outward and downstream direction toward the fan blade platforms.
    Type: Grant
    Filed: September 28, 2016
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Alecu, Ivan Sidorovich Paradiso
  • Patent number: 10967983
    Abstract: There is disclosed a cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft. The cooling system has: a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; a blower outlet defined through a wall of the aircraft and fluidly communicating with the environment; and a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the power plant.
    Type: Grant
    Filed: June 5, 2019
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Luc Dionne
  • Patent number: 10968834
    Abstract: There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.
    Type: Grant
    Filed: June 28, 2019
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Labbe, Lukasz Pokrzywa
  • Patent number: 10968824
    Abstract: A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least two rotary engines is also discussed.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sebastien Bolduc, Mike Fontaine, Luc Landry, Jean Thomassin
  • Patent number: 10968774
    Abstract: There is disclosed an assembly for a gas turbine engine that includes a bearing housing circumferentially extending around a central axis thereof and delimiting a bearing cavity for receiving a bearing therein. A controlled gap seal is secured to the bearing housing, the controlled gap seal including a ring and a runner, the runner rotatable relative to the ring about the central axis, the runner spaced apart from the ring by a gap. The gap defines a fluid passage between the bearing cavity and an environment outside the bearing cavity. At least one baffle is secured to a surface of the bearing housing oriented toward the bearing cavity. The at least one baffle is a fin protruding from the surface and extending into the bearing cavity. The at least one baffle disrupts a cylindricality of the surface. A method of operating the bearing assembly is also disclosed.
    Type: Grant
    Filed: November 20, 2018
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Aldo Abate, Nicola Houle