Search Patents
  • Igniter for gas turbine engine
    Patent number: 11415060
    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: Grant
    Filed: March 29, 2019
    Date of Patent: August 16, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Heat exchanger system for aircraft and associated method of operation
    Patent number: 10900422
    Abstract: The heat exchanger system can have a first conduit extending from at least one first conduit inlet through a heat exchanger to at least two first conduit outlets; a second conduit extending from at least one second inlet through the heat exchanger to at least one second outlet, the first and second conduits disposed adjacent to one another in heat exchange engagement within the heat exchanger; and a bypass conduit extending from the first conduit between the at least one first inlet and the heat exchanger to the first conduit between the heat exchanger and at least one of said at least two first outlets.
    Type: Grant
    Filed: January 31, 2017
    Date of Patent: January 26, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: John Adam Logan, Marc Jordan Adique
  • REDUCED COGGING TORQUE PERMANENT MAGNET MACHINE
    Publication number: 20140145525
    Abstract: An electric machine is formed by a stator and a rotor that is free to rotate about an axis of rotation. The stator may have teeth projecting from a body portion and that define slots for housing electrical windings. The rotor may have a rotor core and a number of magnets supported on a peripheral face of the rotor in substantially contiguous arrangement and of alternating magnetization. The rotor magnets are shaped so that pairs of adjacent magnets oppose one another along magnetic boundary lines that are skewed relative to the slots formed in the body portion of the stator. For example, the shape of the rotor magnets may be arcuate trapezoidal or parallelogramatic. In this configuration, cogging torque experienced by the rotor during operation of the electric machine may be reduced.
    Type: Application
    Filed: November 28, 2012
    Publication date: May 29, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Kevin Allan DOOLEY
  • Air cooling shaft at bearing interface
    Patent number: 9410429
    Abstract: A gas turbine engine including a compressor rotor and a turbine rotor connected by a compressor shaft portion connected to the compressor rotor and a turbine shaft portion connected to the turbine rotor. The compressor shaft portion and the turbine shaft portion are connected axially together by a shaft coupling, between the compressor rotor and the turbine rotor, and at least a bearing rotatably coupled to the compressor shaft portion adjacent the shaft coupling. The compressor shaft and/or the turbine shaft are provided with openings permitting cooling air to enter air passages in the area of the shaft coupling and surrounding the end of the turbine shaft portion, in order to dissipate heat originating at the turbine rotor and thus reducing the thermal stresses at the bearing.
    Type: Grant
    Filed: November 30, 2012
    Date of Patent: August 9, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: John Watson, Guy Bouchard, Daniel Blais
  • Mid turbine frame system and radial locator for radially centering a bearing for gas turbine engine
    Patent number: 8099962
    Abstract: A gas turbine engine has a casing component, such as a mid turbine frame system, which includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing are detachably connected to the outer case and radially extend between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. An arrangement for radially centring the bearing within the outer case is provided, the arrangement including at least three radial locators mounted to the outer case.
    Type: Grant
    Filed: November 28, 2008
    Date of Patent: January 24, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon, Lam Nguyen
  • Fuel manifold with jumper tubes
    Patent number: 9140453
    Abstract: A gas turbine engine fuel delivery system which includes an external fuel manifold fastened to the outer surface of a casing surrounding the combustor of the engine and which includes a plurality of inlet manifold tubes circumferentially disposed in serial flow communication. A plurality of fuel nozzles are mounted to the casing and are axially spaced apart from the fuel manifold on the outer surface of the casing. A plurality of jumper tubes are disposed outside the casing and feed fuel flow from the fuel manifold to the fuel nozzles. The jumper tubes have a rigidity that is less than that of the inlet manifold tubes of the fuel manifold such that the jumper tubes elastically deflect under load.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: September 22, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Aleksandar Kojovic, Saeid Oskooel, Bryan Bond
  • Flow restrictor for lubrication line
    Patent number: 8997449
    Abstract: A flow restrictor is provided for a lubrication circulation system. The flow restrictor comprises a body configured to obstruct a flow of lubricant within the lubricant circulation system. The body has one or more through holes communicating with upstream and downstream portions of the lubrication circulation system. Each of the one or more holes has a cross-sectional area sufficiently small, and a length sufficiently long, to prevent turbulent lubricant flow therethrough at temperatures below a first predetermined reference temperature. The one or more holes have sufficient aggregate cross-sectional area to allow a desired lubricant flow rate through the body at temperatures at or above a second predetermined reference temperature.
    Type: Grant
    Filed: December 22, 2008
    Date of Patent: April 7, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Adam Logan
  • Method to supply oil to a multi-film damper
    Patent number: 10947863
    Abstract: A multi-film oil damper has a housing defining an annular damper cavity having an oil inlet in communication with a source of pressurized oil. A plurality of nested damper rings is disposed within the annular damper cavity, the plurality of nested damper rings defining a plurality of squeeze film annuli. Spacer rings are disposed adjacent opposed ends of the damper rings. A contact surface of the spacer rings extends radially beyond a first cylindrical surface of an associated damper ring for engaging a second cylindrical surface of an adjacent damper ring. Recesses are defined in the second cylindrical surface of the damper rings, the recesses fluidly communicating between the squeeze film annuli and the oil inlet.
    Type: Grant
    Filed: October 18, 2019
    Date of Patent: March 16, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Ivakitch, David Beamish
  • Turbine engine with a thermal valve
    Patent number: 6067791
    Abstract: A turbine engine having interior cavity sealed by a thermally controlled valve is disclosed. The cavity is defined by at least one cylindrical wall portion. The valve comprises an opening in the cylindrical wall portion and a cylindrical band, coaxial and interior to the wall portion. The cylindrical band is made of material having a higher thermal coefficient of expansion than the wall portion. As the temperature of the engine increases, the band expands at a higher rate than the wall, thereby sealing the valve. As the temperature decreases, the band contracts thereby opening the valve. The valve may be used to permit a cavity to be pressurized at low temperatures. The pressure in the cavity may exert a forward load on a thrust bearing, suspending the engine shaft.
    Type: Grant
    Filed: December 11, 1997
    Date of Patent: May 30, 2000
    Assignee: Pratt & Whitney Canada Inc.
    Inventor: Kiritkumar Patel
  • Combined torque measurement and clutch apparatus
    Patent number: 7007560
    Abstract: A method of using a magnetic fluid clutch for torque measurement comprises steps of modulating electric current through a coil of the magnetic fluid clutch to maintain a steady-state quasi-solid phase of a magnetic fluid medium contained within the magnetic fluid clutch when the magnetic fluid clutch is clutched to transmit torque from a torque input end of the clutch to a torque output end of the clutch, thereby ensuring that the torque output end rotates in response to the rotation of the torque input end without relative rotational slippage therebetween; and measuring a deflection value associated with the magnetic fluid clutch. The clutch is thereby used as a combined torque measurement and clutch apparatus.
    Type: Grant
    Filed: October 18, 2004
    Date of Patent: March 7, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Stephen Arthur Anderson
  • Low noise aeroengine inlet system
    Patent number: 10054050
    Abstract: An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor.
    Type: Grant
    Filed: August 19, 2014
    Date of Patent: August 21, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Labrecque, Vincent Couture-Gagnon, Richard Ullyott
  • TRANSIENT GASEOUS FUEL FLOW SCHEDULING
    Publication number: 20230043433
    Abstract: In accordance with at least one aspect of this disclosure, there is provided a fuel control system for gaseous fuel in an aircraft. The system includes a control module operatively connected to a metering device in a fuel flow conduit, the control module operable to control the flow of fuel through the fuel flow conduit. The control module includes an input line operable to receive a command input indicative of a requested engine state. In embodiments, the control module includes a compressibility logic and machine readable instructions. The machine readable instruction can be configured to cause the control module to control the metering device to achieve the requested engine state based on a compressibility factor input from the compressibility logic.
    Type: Application
    Filed: August 3, 2021
    Publication date: February 9, 2023
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Todd Miller, Thomas Dillon, Ezzat Meshkinfam, Lu Xuening
  • Combined hydraulic fluid cooler/tank
    Patent number: 6502630
    Abstract: A convectively-cooled hydraulic fluid tank system comprises a hydraulic fluid tank and a fluid cooler incorporated into the hydraulic fluid tank. The fluid cooler includes a vortex chamber having a wall made of a heat conductive material. An inlet is provided to direct incoming pressurized hydraulic fluid tangentially onto the inner surface of the vortex chamber wall to create a swirled flow of hydraulic fluid against the inner surface of the wall. A cooling structure extends from an exterior surface of the vortex chamber wall to promote heat dissipation.
    Type: Grant
    Filed: December 3, 2001
    Date of Patent: January 7, 2003
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ian Alexander MacFarlane, Keith Martin Morgan, Thomas Francis Haslam-Jones, Nigel Walters, Jean Omer Gagnon
  • Fan nose cone and dynamic tuning of aircrafts
    Patent number: 10947995
    Abstract: A method for tuning a vibration response of an aircraft system is disclosed, where the aircraft system comprises an airframe and at least one engine dynamically coupled, the at least one engine having an engine rotor including a nose cone. The method comprises obtaining a range of frequencies associated with at least one resonance mode of the aircraft system and adding mass within the nose cone to offset at least one dominant excitation frequency of the turbofan engine outside the range of frequencies associated with the at least one resonance mode of the aircraft system. A method of tuning dynamic coupling of an aircraft system comprising an airframe and an engine mounted thereto is also disclosed.
    Type: Grant
    Filed: September 26, 2019
    Date of Patent: March 16, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Thomassin, Lena Raykowski, Gilles Begin, Ahmed Abdelrahman
  • Diffuser pipe with splitter vane
    Patent number: 11215196
    Abstract: A compressor diffuser for a gas turbine engine includes one or more diffuser pipes having a tubular body defining an internal flow passage extending therethrough. The tubular body includes a first portion extending in a first direction, a second portion extending in a second direction different from the first direction, and a curved portion fluidly linking the first portion and the second portion. A splitter vane is disposed within the internal flow passage of the curved portion of the tubular body, the splitter vane defining a convergent flow passage between itself and a radially inner wall of the curved portion, and a divergent flow passage between itself and a radially outer wall of the curved portion.
    Type: Grant
    Filed: January 15, 2020
    Date of Patent: January 4, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Vijay Kandasamy, Koundinya Upadrasta
  • Active coolant flow control for machining processes
    Patent number: 8568198
    Abstract: A system for machining a work-piece is described which includes a machine tool and coolant delivery unit, pressure and flow rate sensors, and a control unit. The control unit controls coolant delivery and is adapted to detect a first anomaly when either a measured flow rate or pressure deviates from target flow rates and pressures by a first predetermined amount, and to detect a second anomaly when the measured flow rate or pressure deviates from the target flow rates and pressures by a second predetermined amount greater than the first. An alarm signal is outputted when the first anomaly is detected, and the machine tool is stopped when the second anomaly is detected.
    Type: Grant
    Filed: July 16, 2010
    Date of Patent: October 29, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: James Leishman, Amr Elfizy
  • System and method for measuring an axial position of a rotating component of an engine
    Patent number: 11428116
    Abstract: Methods and systems for measuring an axial position of a rotating component of an engine are described herein. The method comprises obtaining a signal from a sensor coupled to the rotating component, the rotating component having a plurality of position markers distributed about a surface thereof, the position markers having an axially varying characteristic configured to cause a change in a varying parameter of the signal as a function of the axial position of the rotating component. Based on the signal, the method comprises determining a rotational speed of the rotating component from the signal, determining the varying parameter of the signal, and finding the axial position of the rotating component based on a known relationship between the axial position, the rotational speed, and the varying parameter of the signal.
    Type: Grant
    Filed: November 29, 2019
    Date of Patent: August 30, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Antwan Shenouda, Ella Yakobov
  • Gas turbine engine fluid system with accumulator and hydraulic accessory
    Patent number: 11067004
    Abstract: A fluid system for a gas turbine engine includes a first supply line, a hydraulic accessory actuable by a fluid, and a second supply line fluidly connected the hydraulic accessory and to the first supply line upstream of the component. An accumulator is fluidly connected to the second supply line upstream of the hydraulic accessory. The accumulator is operable to fill a reservoir with the fluid from the first supply line via the second supply line, and to deliver the fluid to the hydraulic accessory via the second supply line. The first supply line may be a fuel or lubricant main supply line of the engine. A method of actuating a hydraulic accessory is also disclosed.
    Type: Grant
    Filed: March 27, 2018
    Date of Patent: July 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Nicholas Ngoly, Simon Hartropp, Andrew Walz, Roger Lachance
  • Rotary internal combustion engine with pilot subchamber and ignition element
    Patent number: 10006359
    Abstract: A rotary engine including an insert in one of the walls of the outer body. The insert has a pilot subchamber defined therein communicating with the internal cavity and includes a subchamber wall surrounding the pilot subchamber. A main fuel injector is in communication with the internal cavity at a location spaced apart from the insert. A pilot fuel injector is in communication with the pilot subchamber. A heating element extends within the subchamber wall completely outside of the pilot subchamber, in heat transfer communication with the subchamber wall. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.
    Type: Grant
    Filed: May 2, 2016
    Date of Patent: June 26, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Gaul, Andre Julien, Bruno Villeneuve
  • System and method for measuring an axial position of a rotating component of an engine
    Patent number: 11814970
    Abstract: Methods and systems for measuring an axial position of a rotating component of an engine are described herein. The method comprises obtaining a signal from a sensor coupled to the rotating component, the rotating component having a plurality of position markers distributed about a surface thereof, the position markers having an axially varying characteristic configured to cause a change in a varying parameter of the signal as a function of the axial position of the rotating component. Based on the signal, the method comprises determining a rotational speed of the rotating component from the signal, determining the varying parameter of the signal, and finding the axial position of the rotating component based on a known relationship between the axial position, the rotational speed, and the varying parameter of the signal.
    Type: Grant
    Filed: July 11, 2022
    Date of Patent: November 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Antwan Shenouda, Ella Yakobov
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