Search Patents
  • AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE
    Publication number: 20140012481
    Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.
    Type: Application
    Filed: September 13, 2013
    Publication date: January 9, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
  • Laser drilling methods of shallow-angled holes
    Patent number: 8631557
    Abstract: A method for providing a shallow-angled hole through a thermal barrier coated component in accordance with one aspect thereof, includes a step of applying a pulse laser beam to pre-drill the hole through a base metal of the component. A thermal barrier coating is then applied to the base metal, covering the pre-drilled hole in the base metal. A further step is conducted to apply the pulse laser beam through the thermal barrier coating a location to coincide with pre-drilled hole in the base metal in order to complete the formation of the hole extending through the component.
    Type: Grant
    Filed: July 19, 2011
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Amr Elfizy, Ghislain Hardy, Sylvain Cournoyer
  • Aircraft propulsion system with intermittent combustion engine(s)
    Patent number: 11719166
    Abstract: An aircraft system is provided that includes a first propulsor rotor, a second propulsor rotor, a drivetrain and an intermittent combustion engine. The first propulsor rotor is rotatable about a first propulsor axis. The second propulsor rotor is rotatable about a second propulsor axis. The drivetrain includes a drive structure and a transmission. The drive structure is rotatable about a drive axis that is angularly offset from the first propulsor axis and the second propulsor axis. An output of the transmission is coupled to the first propulsor rotor and the second propulsor rotor through the drive structure. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the drivetrain.
    Type: Grant
    Filed: July 15, 2022
    Date of Patent: August 8, 2023
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Richard Freer
  • Composite fire shield
    Patent number: 8222165
    Abstract: A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fiber cloth impregnated with a sacrificial resin which has a melting point that is below that of the fiber cloth. When exposed to fire, the fiber cloth remains substantially intact for at least the minimum period of time while the sacrificial resin is allowed to be at least partially consumed by the fire, such that the protective fire shield is partially sacrificed.
    Type: Grant
    Filed: October 27, 2008
    Date of Patent: July 17, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Bryan William Olver
  • LUBRICANT PUMP SYSTEM AND METHOD FOR AIRCRAFT ENGINE
    Publication number: 20230417153
    Abstract: Lubricant pump systems and associated methods for aircraft engines are provided. The method includes receiving an input torque, dividing the input torque between a first load path receiving a first portion of the input torque, and a second load path receiving a second portion of the input torque. A first lubricant pump of the aircraft engine is driven via the first load path using the first portion of the input torque. A second lubricant pump of the aircraft engine is driven via the second load path using the second portion of the input torque. When a malfunction of the second lubricant pump occurs, the method includes ceasing to drive the first lubricant pump and the second lubricant pump using the input torque.
    Type: Application
    Filed: September 12, 2023
    Publication date: December 28, 2023
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Hervé TURCOTTE
  • Methods for measuring part size and runout
    Patent number: 11230393
    Abstract: A part measuring kit for a rotary table on a machine bed includes a part fixture mountable on the rotary table for retaining a part to be measured and/or an object having known dimensions. The kit further includes a measuring device mountable on the machine bed and movable relative to the rotary table for taking measurements of the part to be measured and/or the object having known dimensions, wherein the rotary table is rotatable between each taken measurement. The kit further includes a calibration offset calculator for calculating a calibration offset for the measuring device by comparing taken measurements of the object having known dimensions with the known dimensions, and correcting taken measurements of the part to be measured via the calculated calibration offset.
    Type: Grant
    Filed: July 23, 2020
    Date of Patent: January 25, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Rachid Guiassa, Lafleche Gagnon
  • INTEGRATED TURBINE EXHAUST STRUTS AND MIXER OF TURBOFAN ENGINE
    Publication number: 20150075169
    Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and an annular shroud with the mixer attached to a downstream end of the shroud, the shroud and the mixer surrounding the hub to form an annular exhaust gas duct positioned radially therebetween, a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located within an axial length of the mixer between an upstream end and a downstream end of the mixer, the deswirling struts each having a cambered profile and extending radially across the annular exhaust gas duct and interconnecting the mixer and the hub.
    Type: Application
    Filed: May 26, 2014
    Publication date: March 19, 2015
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Mark Huzzard CUNNINGHAM, Edward Parker VLASIC, Sami GIRGIS
  • Internal manifold with fuel inlet
    Patent number: 10294865
    Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: May 21, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Cooler in nacelle with radial coolant
    Patent number: 8266888
    Abstract: A cooling system in an aircraft gas turbine engine includes a heat exchanger positioned within an annular nacelle space surrounding a bypass duct of the engine. The heat exchanger has a radial coolant passage extending between the bypass duct and ambient air surrounding the nacelle, and a flow passage extending substantially normal to the radial passage for direction of a fluid to be cooled therethrough. A configuration of this nature may assist in defining a no-flow length of the heat exchanger in a third direction normal to the other two mentioned directions, which may allow for improved performance within a given radial envelope.
    Type: Grant
    Filed: June 24, 2010
    Date of Patent: September 18, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Xiaoliu Liu
  • Airfoil for gas turbine engine
    Patent number: 10718216
    Abstract: An airfoil for a gas turbine engine including a tip extension disposed at the tip of the airfoil body. The tip extension extends from the suction side surface and/or the pressure side surface and defines a tip thickness that is larger than a true thickness of the airfoil body. The true thickness is defined within a plane perpendicular to a root axis and extending transversely to the airfoil chord around a midpoint thereof. The tip extension includes a side transitional surface forming a curve extending tangentially from the side surface and/or the pressure side surface. The tip thickness increases over a radial dimension in the plane that is at least 2 times the true thickness.
    Type: Grant
    Filed: August 30, 2018
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean Rockarts, Peter Townsend
  • Epicyclic gear train with balanced carrier stiffness
    Patent number: 10760677
    Abstract: An epicyclic gear train including a central sun gear, an outer ring gear, and a number of planet gears which are mounted to a planet carrier. The planet carrier includes a centrally disposed torque transfer coupling with a torque transmission point at an axial end thereof. First and second carrier plates extend radially from the torque transfer coupling and are axially spaced apart to support the planet gears therebetween at aligned gear mounting points. The first carrier plate is closer to the torque transfer point than the second carrier plate. The second carrier plate has a stiffness that is greater than that of the first carrier plate.
    Type: Grant
    Filed: January 31, 2018
    Date of Patent: September 1, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Louis Brillon, Michel Desjardins
  • Conduit bracket for a gas turbine engine
    Patent number: 11852031
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a static structure, a conduit and a bracket. The static structure includes a port. The conduit extends longitudinally through the port. The bracket couples the conduit to the static structure. The bracket includes a first base mount, a second bade mount, a conduit mount, a first damper and a second damper. The first base mount is attached to the static structure. The second base mount is attached to the static structure. The conduit mount is mechanically coupled with the conduit. The first damper is between the first base mount and the conduit mount. The second damper is between the second base mount and the conduit mount.
    Type: Grant
    Filed: August 3, 2021
    Date of Patent: December 26, 2023
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Mateusz Pelc, Julien Girard
  • Planetary gearbox for gas turbine engine
    Patent number: 11377199
    Abstract: An aircraft includes first and second engines, one or more aircraft rotors associated with the first and second engines, a first epicyclic gearbox having: a) an output operatively connected at least one of the one or more aircraft rotors, and b) an input defined by a sun gear of the first epicyclic gearbox; and a second epicyclic gearbox having: a) an output operatively connected to at least one of the one or more aircraft rotors, and b) an input defined by a sun gear of the second epicyclic gearbox. Output of the first epicyclic gearbox is defined by the carrier. Output of the second epicyclic gearbox is defined by its ring gear. A multi-engine aircraft and a method of operating a multi-engine aircraft are also described.
    Type: Grant
    Filed: March 27, 2020
    Date of Patent: July 5, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Lazar Mitrovic
  • Anti-cavitation device for oil dampers
    Patent number: 10767511
    Abstract: The disclosure relates to an anti-cavitation device for impeding gas intrusion into oil dampers that support bearings and a rotating shaft. The oil film damper includes an annulus and a pair of piston rings between a structural support and the bearing housing. The piston rings define the axial boundaries of the oil filled annulus. An oil inlet between the pair of piston rings is in communication with a source of pressurized oil. An oil seal is axially spaced from each piston ring defining an annular oil filled reservoir external to each piston ring. The oil seal acts as a one way check valve to impede gas incursion into the oil reservoir and oil filled annulus.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: September 8, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Charles Litalien
  • System and method for operating a multi-engine rotorcraft for ice accretion shedding
    Patent number: 11535386
    Abstract: There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.
    Type: Grant
    Filed: November 1, 2019
    Date of Patent: December 27, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Philippe Beauchesne-Martel, Mark Cunningham
  • Fastening system for fan and shaft interconnection
    Patent number: 8932022
    Abstract: A fan and shaft assembly for a turbofan gas turbine engine comprises a shaft and a fan. Sets of aligned throughbores are respectively of the shaft and the fan, at a junction between the shaft and the fan. Fastening systems are provided for the sets of aligned throughbores. Each fastening system comprises a sleeve received in one of the sets of aligned throughbores and sized to fit without play in the set of aligned throughbores. A head of the sleeve abuts a surface at the junction between the shaft and the fan. A fastener is inserted in the sleeve and extends beyond both ends of the sleeve to clamp the fan to the shaft, the fastener being loosely received in the sleeve. A method for replacing a component of a fastening system retaining a fan to a shaft is provided as well.
    Type: Grant
    Filed: February 3, 2012
    Date of Patent: January 13, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Richard Ivakitch, Andreas Eleftheriou, Alain Carrieres
  • System and method for an engine controller based on acceleration power
    Patent number: 10480421
    Abstract: Systems and methods for controlling an gas turbine engine are provided. The method comprises receiving a requested engine speed and obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow. A required fuel flow to obtain an engine acceleration is determined as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow. A command to a fuel flow metering valve is output in accordance with the required fuel flow.
    Type: Grant
    Filed: November 25, 2016
    Date of Patent: November 19, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gabriel Meunier, Alexandre Charest, Sylvain Lamarre
  • Gas turbine engine exhaust ejector/mixer
    Patent number: 10619596
    Abstract: An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: April 14, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Guy Lefebvre, Patrick L'Esperance, Gabriel Emard-Parent
  • Gas turbine engine exhaust ejector/mixer
    Patent number: 9745919
    Abstract: An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: August 29, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Guy Lefebvre, Patrick L'Esperance, Gabriel Emard-Parent
  • Combustor floating collar mounting arrangement
    Patent number: 11125436
    Abstract: A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Maximilian Baranowicz, Si-Man Amy Lao, Oleg Morenko
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