Search Patents
  • Engine assembly for an auxiliary power unit
    Patent number: 10501200
    Abstract: An auxiliary power unit having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft drivingly engaged to the engine shaft, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.
    Type: Grant
    Filed: June 11, 2018
    Date of Patent: December 10, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Richard Ullyott, Anthony Jones, Andre Julien, Jean Thomassin
  • Blade angle position feedback system with extended markers
    Patent number: 10829201
    Abstract: A blade angle feedback assembly for an aircraft-bladed rotor and an aircraft-bladed rotor system are provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor, the feedback device having a root surface having an edge. At least one position marker extends from the root surface and extends laterally beyond the edge. At least one sensor is mounted adjacent the feedback device and configured to detect a passage of the at least one position marker as the feedback device rotates about the longitudinal axis.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: November 10, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Dana Tomescu
  • Connector for multi-phase conductors
    Patent number: 8608496
    Abstract: A connector for multi-phase conductors. The connector includes conductors for conducting multi-phase currents, and at least one conductive plate corresponding to each phase. Each conductive plate defines apertures for the conductors to pass through, there being at least one aperture in each conductive plate for each respective conductor. Each conductive plate includes at least one connecting member for forming an external electrical connection. Each conductor passes through a respective aperture of each conductive plate. Each conductor is selectively coupled to form electrical connection only to a conductive plate corresponding to the respective phase of the conductor.
    Type: Grant
    Filed: April 25, 2012
    Date of Patent: December 17, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Antwan Shenouda, Steve Strecker, Nathan Tomes
  • Air inlet for a gas turbine engine
    Patent number: 10385785
    Abstract: A radial air inlet for a gas turbine engine. The air inlet has an inlet duct defined between two axially-spaced radially-extending annular walls and has a plurality of circumferentially-spaced axially-extending struts extending between the annular walls adjacent a radially-outer portion of the air inlet. At least one of the struts has an internal passage extending between a first opening in a forward end of the strut and a second opening in an aft end of the strut, the first and second openings being axially spaced apart. A transmission shaft extends through the internal passage of said strut.
    Type: Grant
    Filed: July 17, 2017
    Date of Patent: August 20, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ian MacFarlane, Lazar Mitrovic
  • COMPRESSOR VARIABLE VANE ASSEMBLY
    Publication number: 20150275916
    Abstract: A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections the inner and/or outer shroud which protruded into the annular gas path such as to ensure that a radial clearance gap, defined between the projections and a vane airfoil overhang portion, remains substantially constant throughout a substantial portion of the vane pivot arc of the variable vane. The method includes forming one cavities within the shroud, the cavities isolated from the annular gas path and disposed radially beneath at least each of the projections, and providing one or more structural reinforcing elements within the cavities.
    Type: Application
    Filed: March 28, 2014
    Publication date: October 1, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Andrew R. MARSHALL, David Menheere
  • Active turbine or compressor tip clearance control
    Patent number: 9598974
    Abstract: A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.
    Type: Grant
    Filed: February 25, 2013
    Date of Patent: March 21, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, Terrence Lucas, Thomas Francis Haslam-Jones, Danny Mills, Guy Bouchard
  • Through-flow gas turbine engine with electric motor and electric generator
    Patent number: 11686253
    Abstract: A through-flow gas turbine engine includes a core comprising multiple spools rotatable about a center axis. An accessory gearbox (AGB) is drivingly engaged to the core and disposed aft of the outlet. A reduction gearbox (RGB) is drivingly engaged to the core and disposed forward of the inlet. The RGB has an RGB output to provide rotational output to a rotatable load. An electric motor is drivingly engaged to the rotatable load. An electric generator is configured to provide electrical power to the electric motor. the electric motor and the electric generator are disposed axially adjacent one another, and axially between the outlet and the AGB.
    Type: Grant
    Filed: May 17, 2022
    Date of Patent: June 27, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Guy Lefebvre
  • Combustor dome heat shield
    Patent number: 9982890
    Abstract: A combustor heat shield has lips with fins distributed on the lips. The lip-fins have an extended end portion projecting rearwardly from the back face of the heat shield. Impingement jets may be directed against the rearwardly extended end portions of the lip-fins to enhance cooling. The heat shield may define a fuel nozzle opening surrounded by a rail on the back side of the heat shield. Impingement holes or slots may be defined in the rail for allowing cooling air passing therethrough to impinge upon the lip-fins.
    Type: Grant
    Filed: November 20, 2013
    Date of Patent: May 29, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Robert Sze, Sri Sreekanth
  • Method of calibrating a machine having at least two rotation axes
    Patent number: 11487268
    Abstract: The method can include measuring the tridimensional positions of a reference feature for a first at least three different angular positions of the reference feature around the first rotation axis and a same first reference angular position around the second rotation axis, the reference feature being fixed relative to the component; and measuring the tridimensional positions of the reference feature for a second at least three different angular positions of the reference feature around the first rotation axis and a same second reference angular position around the second rotation axis.
    Type: Grant
    Filed: July 25, 2019
    Date of Patent: November 1, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mario Blais, Clement Drouin Laberge, Visal Ing
  • Communication module for transmission of aircraft data
    Patent number: 11916648
    Abstract: Herein provided is an interface for use in transmitting data from an aircraft including a first connector configured for physically and removably coupling a communication module to a communication system which obtains the data on-board the aircraft from at least one data source within the aircraft, and a second connector for digitally coupling the communication module to a processing unit of the communication module producing at least one message for transmission based on the data, the at least one message comprising information of interest identified based on the data. The interface is configured for conducting the at least one message from the processing unit to at least one radio via the second connector.
    Type: Grant
    Filed: July 4, 2022
    Date of Patent: February 27, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Jonathan Mark Miller
  • Rotary internal combustion engine with phasing gear
    Patent number: 9366138
    Abstract: In one aspect, described is a rotor of a rotary internal combustion engine, including a phasing gear with an annular meshing section including a plurality of radially inwardly oriented teeth and an annular attachment section connected to the meshing section and coaxial therewith, the attachment section being offset axially inwardly from the teeth and having at least a portion thereof located radially inwardly of the teeth, and a fastener apparatus connecting the phasing gear to the rotor body, the fastener apparatus engaging the rotor body radially inwardly of the teeth.
    Type: Grant
    Filed: October 14, 2011
    Date of Patent: June 14, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, Sebastien Bolduc, Mike Fontaine
  • Fault detection system and method for liquid level sensing device
    Patent number: 11125603
    Abstract: A method and system are described for detecting a fault of a fluid level sensing device associated with an aircraft engine, the fluid level sensing device arranged to measure a variance in a fluid level. The method comprises triggering a timer, while the timer is running, receiving a measurement indicative of the fluid level from the fluid level sensing device, resetting the timer when at least one timer-reset condition has been met, and outputting a fault signal when the timer reaches a timer threshold.
    Type: Grant
    Filed: June 21, 2019
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Benjamin Bregani, Sean McCarthy, Nicolas Renard, Andrew Ghattas
  • Fuel nozzle
    Patent number: 9765974
    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: September 19, 2017
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Yen-Wen Wang, Nigel Davenport, Eduardo Hawie
  • Method of priming a pump of an aircraft engine
    Patent number: 11603842
    Abstract: A method of priming a pump includes supplying lubricant, via a priming flow path, into an interface defined between a first part of a shaft of the pump and a second part of the shaft coaxially engaged with the first part of the shaft to define the pump, the first part of the shaft rotatable about a rotation axis relative to the second part of the shaft, and supplying lubricant into the interface via a lubrication flow path that is different from the priming flow path. A method of lubricating an aircraft motor of an aircraft engine, and a machine for an aircraft engine are also described.
    Type: Grant
    Filed: August 14, 2019
    Date of Patent: March 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Dana Tomescu, Daniel Alecu
  • Electric machine systems comprising a stator common to the plurality of rotors
    Patent number: 11894742
    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: April 8, 2021
    Date of Patent: February 6, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Latulipe, Richard Freer
  • Method and system for regulating oil flow to an engine
    Patent number: 11371436
    Abstract: Systems and methods for regulating oil flow to an engine are described herein. An oil pressure target for the engine is determined based on one or more engine operating parameters. Oil flow to the engine is controlled based on the oil pressure target. Closed-loop feedback of oil pressure of the engine is obtained from at least one sensor during the controlling of the oil flow to the engine. A pressure difference between the oil pressure target and the closed-loop feedback of the oil pressure of the engine is determined. The oil flow to the engine is adjusted based on the pressure difference.
    Type: Grant
    Filed: January 16, 2020
    Date of Patent: June 28, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Pierre-Yves Legare, Eric Langevin, Alain Martel
  • Shaft event detection in gas turbine engines
    Patent number: 10436060
    Abstract: There is described herein methods and systems for detecting a shaft event in a gas turbine engine comprising a power turbine having a first shaft extending in a first direction and a second shaft extending in a second direction opposite from the first direction. A first speed measurement is obtained at a first location along the first shaft and a second speed measurement is obtained at a second location along the second shaft. A speed ratio is determined between the first speed measurement and the second speed measurement, and is compared to a detection threshold. The shaft event is detected when the speed ratio is beyond the detection threshold.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: October 8, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Dubreuil, Johnny Vinski, Michel Desjardins
  • NESTED CONTROL LOOP STRUCTURE FOR HYBRID PROPULSION SYSTEM
    Publication number: 20230058484
    Abstract: In accordance with at least one aspect of the present disclosure, there is provided a method for controlling power in an aircraft. The method includes, monitoring an electric energy storage module electrically connected to an electrical bus for an exceedance of a first current limit and monitoring a generator module connected to the electrical bus for an exceedance of a second current limit. If the current limit of either of the electric energy storage module or the generator module is exceeded by a predetermined exceedance amount, the method includes reducing a power consumption for an electric machine by a predetermined bias until the exceedance of the electrical energy storage and the exceedance of the generator module are both less than or equal to zero.
    Type: Application
    Filed: August 17, 2021
    Publication date: February 23, 2023
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Richard Freer
  • Ball bearing rear inner ring with oil circumferential groove
    Patent number: 11215231
    Abstract: An inner ring for a bearing assembly comprises an inner circumferential surface disposed between a first axial end and a second axial end. A circumferential slot is disposed in the inner circumferential surface adjacent the second axial end. At least one radial passage is disposed within the inner ring and is in fluid communication with the circumferential slot. At least one axial slot extends axially along the inner circumferential surface from a respective opening in the first axial end to the circumferential slot. At least one of the radial passage is circumferentially offset from each at least one axial slot.
    Type: Grant
    Filed: April 15, 2020
    Date of Patent: January 4, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Cédric Poirier
  • Compressor turbine blade airfoil profile
    Patent number: 10513929
    Abstract: A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: August 31, 2017
    Date of Patent: December 24, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Niloofar Moradi, Krishan Mohan, Panagiota Tsifourdaris, Sami Girgis, Vincent Paradis, Robert Huszar, Jasrobin Grewal
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