Search Patents
  • Inertial separator
    Patent number: 4592765
    Abstract: A particle separator for a gas turbine engine is described having an inlet passage to the compressor of the gas turbine engine, with the inlet passageway being defined by an inner wall and an outer wall. The inner wall diverges outwardly to form a throat with a diverging outer wall and converges inwardly downstream thereof. A first bypass opening is provided immediately upstream of the diverging inner wall, whereby solid and liquid particles can be diverted and passed overboard. A splitter ring is provided in the inlet passageway downstream of the converging inner wall, such that the finer particles escaping from the first bypass openings would be separated by the splitter ring.
    Type: Grant
    Filed: January 15, 1985
    Date of Patent: June 3, 1986
    Assignee: Pratt & Whitney Canada Inc.
    Inventors: Daniel S. Breitman, Ernest G. Dueck
  • Method to seal damper cavity of multi-film oil damper
    Patent number: 10808755
    Abstract: A multi-film oil damper suited for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall and radially extending side walls; an inner damper ring; an outer damper ring disposed between the inner damper ring and the radially outward wall of the annular damper cavity; wherein the annular damper cavity has an oil inlet in communication with a source of pressurized oil; and wherein a radial thickness of the inner damper ring exceeds a radial thickness of the outer damper ring.
    Type: Grant
    Filed: March 4, 2019
    Date of Patent: October 20, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Veitch, David Beamish
  • 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
  • Turbofan engine and core link therefore
    Patent number: 11111856
    Abstract: The turbofan engine can have a core engine, a bypass duct surrounding the core engine, an annular bypass flow path between the bypass duct and the core engine, and a plurality of core links extending across the bypass path and supporting the core engine relative to the bypass duct, and a fluid passage having a heat exchange portion in a given one of the core links, the heat exchange portion being configured for heat exchange with the bypass flow path, an inlet leading into the given core link and to the heat exchange portion, and an outlet extending from the heat exchange portion and out of the given core link.
    Type: Grant
    Filed: March 4, 2019
    Date of Patent: September 7, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventor: Bryan William Olver
  • 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
  • Turbine shroud segment sealing
    Patent number: 9850775
    Abstract: An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments. The blade shroud segments integrally extend downstream from the vane shroud segments and each pair of circumferentially adjacent blade shroud segments defines an inter-segment gap. At least one slot extends axially from a location downstream of the vane shroud segments to an aft end of the blade shroud segment. The inter-segment gaps and slots are sealed by a sealing band mounted around the full circumference of the integrated shroud structure.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: December 26, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: John Pietrobon, Remy Synnott
  • 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
  • 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
  • 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
  • Through-flow gas turbine engine with electric motor and electric generator
    Patent number: 11384693
    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. One of the electric motor and the electric generator is disposed axially between the outlet and the AGB and the other of the electric motor and the electric generator is disposed axially between the inlet and the RGB.
    Type: Grant
    Filed: June 10, 2020
    Date of Patent: July 12, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Guy Lefebvre
  • 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
  • Method of manufacturing a rotary engine casing
    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
  • 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
  • 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
  • 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
  • Lubrication system with porous element
    Patent number: 8752673
    Abstract: A lubrication system for a gas turbine engine including at least one porous element located in a cavity containing at least one rotating component receiving a flow of the lubricant, the porous element being located across a path taken by a portion of the lubricant expelled from the at least one respective rotating component such that the portion of the lubricant circulates therethrough, the at least one porous element being made of a material resistant to a temperature of the lubricant, the at least one porous element reducing a velocity of the portion of the lubricant circulating therethrough.
    Type: Grant
    Filed: August 27, 2009
    Date of Patent: June 17, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Patrick Thivierge, Mélanie Papillon, Pierre Gauvin, Patrick Arkinson, Robert Scandella, Tom Haslam-Jones, Ritchie Domingo
  • 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
  • Health monitoring of igniters
    Patent number: 9135755
    Abstract: Methods and associated devices useful for the health monitoring of igniters of gas turbine engines are disclosed. Exemplary embodiments disclosed include the use of an accumulated spark count to an igniter to obtain an indication of wear on the igniter and/or the remaining life of the igniter. An exemplary method disclosed includes: receiving one or more signals indicative of a commanded spark count to the igniter for one or more ignition events; processing the one or more signals indicative of the commanded spark count to the igniter, determining a total accumulated commanded spark count to the igniter; and generating one or more signals indicative of at least one of an estimated wear on the igniter or an estimated remaining life of the igniter based on the total accumulated commanded spark count to the igniter.
    Type: Grant
    Filed: August 2, 2013
    Date of Patent: September 15, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michael Youssef
  • 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
  • DUAL CYCLE INTERCOOLED HYDROGEN ENGINE ARCHITECTURE
    Publication number: 20230133397
    Abstract: In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.
    Type: Application
    Filed: December 28, 2022
    Publication date: May 4, 2023
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Scott Smith
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