Search Patents
  • 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 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
  • 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
  • Inspecting an interior of a gas turbine engine apparatus
    Patent number: 11933690
    Abstract: During an inspection method, an inspection scope is inserted into an interior of an apparatus of a gas turbine engine. An image of the interior of the apparatus is captured to provide/output image data. A location of the inspection scope within the interior of the apparatus when the image is captured is determined to provide location data, where the determining of the location includes comparing the image data to model data from a model of the apparatus. During the course of inspection, movement of the inspection scope is tracked within the interior of the apparatus using the location data. The location data may be derived by feature recognition and/or motion tracking of live feed from a scope video output to features available in a field of view within duplicate CAD model.
    Type: Grant
    Filed: October 8, 2021
    Date of Patent: March 19, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Justin Byers
  • 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
  • Electric distributed propulsion using exhaust recovery power
    Patent number: 11926426
    Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.
    Type: Grant
    Filed: March 19, 2021
    Date of Patent: March 12, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Thomassin, Todd A. Spierling
  • 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
  • Gas turbine engine exhaust case with blade shroud and stiffeners
    Patent number: 11959390
    Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes a bladed rotor rotatable about an axis, and an engine case. The engine case includes an outer duct wall, a first circumferential stiffener, a second circumferential stiffener and a plurality of axial stiffeners. The outer duct wall forms a shroud around the bladed rotor. The first circumferential stiffener extends circumferentially about the outer duct wall. The second circumferential stiffener extends circumferentially about the outer duct wall. The axial stiffeners are arranged circumferentially about the outer duct wall. Each of the axial stiffeners extends axially between the first circumferential stiffener and the second circumferential stiffener.
    Type: Grant
    Filed: August 9, 2022
    Date of Patent: April 16, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Philippe Savard, Guy Lefebvre
  • 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
  • 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
  • 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
  • Gas turbine internal manifold mounting arrangement
    Patent number: 7721546
    Abstract: A mounting system for an annular internal fuel manifold of a gas turbine engine includes three supports equally spaced apart about the annular fuel manifold, the three supports having at least two pin supports disposed between the fuel manifold and a surrounding gas generator casing. Each pin support includes a radially extending pin co-operating with an aligned ring slidingly disposed around the pin for relative sliding displacement therebetween. The pin supports providing axial constraint while permitting the fuel manifold to radially displace relative to the surrounding gas generator casing due to thermal size change.
    Type: Grant
    Filed: July 19, 2006
    Date of Patent: May 25, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jason Fish, Bhawan Patel
  • Clutch device for gas turbine engines
    Patent number: 10683900
    Abstract: A clutch device for a gas turbine engine having a sliding coupling mounted to the engine and slidingly displaceable therein. The sliding coupling is mountable between the gearbox and the output shaft. The sliding coupling is continuously engageable with the gearbox and is selectively engageable with the output shaft to mechanically couple the output shaft to the gearbox. The sliding coupling is slidingly displaceable between a first position in which the sliding coupling is mechanically coupled to the output shaft to transmit a rotational drive of the output shaft to the gearbox, and a second position in which the sliding coupling is disengaged from the output shaft. A piston is disposed within the engine and acts on the sliding coupling to displace the sliding coupling to at least the second position.
    Type: Grant
    Filed: April 11, 2017
    Date of Patent: June 16, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Keith Morgan
  • Connecting arrangement between components of an aircraft engine
    Patent number: 11732609
    Abstract: An aircraft engine comprises a casing extending circumferentially around a central axis. A support flange is secured to the casing and extends circumferentially around the axis. The support flange has an inner and an outer flange face. A component is drivingly engaged by a shaft of the engine. The component has a connecting section extending around the central axis. The connecting section has a connecting face. The inner flange face is in abutment against the connecting face. A retaining ring extends circumferentially around the central axis. The retaining ring is in abutment against the outer flange face of the support flange. The retaining ring has a coefficient of thermal expansion, which is less than that of the support flange.
    Type: Grant
    Filed: October 29, 2021
    Date of Patent: August 22, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Menheere, Daniel Alecu
  • Systems and methods for detecting chips in fluid of aircraft engine
    Patent number: 10197488
    Abstract: There is described herein methods and systems for detecting electrically-conductive particles (chips) in fluid of an aircraft engine. The method comprises applying a plurality of excitation currents Ii across a magnetic chip detector mounted to a fluid system of the aircraft engine and measuring a corresponding plurality of resistance values Ri, where i is an integer that varies from 1 to N, and where N corresponds to a number of different excitation currents applied across the magnetic chip detector. The method further comprises determining a chip size indication Y from the plurality of resistance values Ri, and detecting a chip in the fluid when the chip size indication Y exceeds a threshold Ythres.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: February 5, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michael Youssef
  • AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE
    Publication number: 20120029786
    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: July 26, 2011
    Publication date: February 2, 2012
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
  • Aircraft intake duct with passively movable flow restrictor
    Patent number: 11919654
    Abstract: An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.
    Type: Grant
    Filed: August 5, 2022
    Date of Patent: March 5, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Eray Akcayoz
  • Feedback system for pitch-adjustable blades of aircraft bladed rotor
    Patent number: 10889367
    Abstract: Systems and methods for providing pitch position feedback for pitch-adjustable blades of an aircraft bladed rotor are disclosed. In one embodiment, the systems include a sensor comprising a magnet having a magnetic field, a pole piece coupled to a first pole of the magnet and directing the magnetic field toward the feature and a coil mounted in the magnetic field. The coil generates a sensor signal indicative of a variation in the magnetic field caused by movement of the feature in the magnetic field. The sensor also includes a magnetic shield mounted in the magnetic field. The magnetic shield defines a magnetic return path for some magnetic flux of the magnetic field exiting the pole piece toward an opposite second pole of the magnet.
    Type: Grant
    Filed: April 24, 2017
    Date of Patent: January 12, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Kudrna, Ian Farrell
  • HYBRID ELECTRIC AIRCRAFT AND POWERPLANT ARRANGEMENTS
    Publication number: 20210061481
    Abstract: A hybrid electric aircraft powerplant arrangement can include a first wing pair of powerplants for a first wing of an aircraft, the first wing pair comprising a first electric powerplant configured to drive a first air mover and a first heat engine powerplant configured to drive a second air mover separate from the first air mover. The arrangement can include a second wing pair of powerplants for a second wing of the aircraft, the second wing pair comprising a second electric powerplant configured to drive a third air mover separate from the first and second air movers, and a second heat engine powerplant configured to drive a fourth air mover separate from the first, second, and third air movers.
    Type: Application
    Filed: August 20, 2020
    Publication date: March 4, 2021
    Applicants: Pratt & Whitney Canada Corp., Hamilton Sundstrand Corporation
    Inventors: Jean Thomassin, Todd A. Spierling
  • Device for controlling air flow in a turbine blade
    Patent number: 6176677
    Abstract: The present invention relates to gas turbines and more particularly to a device for controlling the flow of cooling air through a flowpath in a turbine blade. The device can be inserted in the inlet opening of the blade flowpath and be retained therein. The device comprises a plug member for adjusting the flow of cooling air through the flowpath. The plug member comprises a retaining portion for retaining the plug member at the inlet opening of the flowpath and a blocking portion inserted within the flowpath for reducing the cross-sectional area of the inlet opening. Such a device is inexpensive and can be easily inserted in the inlet opening of a blade flowpath and retained therein.
    Type: Grant
    Filed: May 19, 1999
    Date of Patent: January 23, 2001
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andr{acute over (e)} Ch{acute over (e)}vrefils, Daniel Gheorghe Grigore
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