Search Patents
  • Method of assembling a capacitor assembly
    Patent number: 9761375
    Abstract: A method of assembling a capacitor assembly comprises positioning a plurality of capacitors in respective sockets formed in a non-conductive matrix by vibrating the plurality of capacitors and disposing the array of capacitors and the non-conductive matrix between a positive terminal plate and a negative terminal plate. The capacitors are electrically coupled with the positive terminal plate and the negative terminal plate and mechanically secured between the positive terminal plate and the negative terminal plate. The array of capacitors includes a void cooperating with a first opening in the positive plate and a second opening in the negative plate to form a passage. The void includes a location where at least one capacitor is omitted from the array.
    Type: Grant
    Filed: May 15, 2014
    Date of Patent: September 12, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kevin Allan Dooley, Joshua Bell
  • Composite fan case with nanoparticles
    Patent number: 11391297
    Abstract: A composite case for a gas turbine engine includes an inner structure assembly defining an impact containment zone. The inner structure assembly is configured to circumscribe a plurality of rotatable blades of the gas turbine engine and to receive blade fragments in an event of blade failure. The inner structure assembly includes one or more layers containing a resin impregnated therein, and an outer structure assembly surrounding the inner structure assembly and integrally molded thereon. The outer structure assembly includes one or more layers containing a resin impregnated therein. One or more layers of the inner and the outer structure assemblies include resin reinforced by nanoparticles.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Kin-Leung Cheung
  • CUP MILL FOR AIRFOILS
    Publication number: 20080131216
    Abstract: A cup milling cutter for machining an integrated bladed rotor is provided a plurality of cutting inserts removably attached to a cup shaped body to form a virtual cutting ring about an axis of rotation at the open end of the cup shaped body when the cup shape body is rotated by a drive spindle. The virtual cutting ring has outer and inner diameter cutting edges and a middle cutting edge therebetween. The virtual cutting ring is sized in a width greater than the thickness of the open end of the cup shaped body to permit the virtual cutting ring in a multi-axis simultaneous motion, to machine the airfoils of the integrated bladed rotor using the respective cutting edges without any interference.
    Type: Application
    Filed: December 5, 2006
    Publication date: June 5, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Ioan SASU, Bertrand TURCOTTE
  • Compact torque measurement system
    Patent number: 4682505
    Abstract: A compact torque measuring device for a gas turbine engine which has an output shaft. The torque measurement device includes a pair of tubular concentric shafts of elastic deformable material. The inner shaft is fixed to the output shaft and includes peripheral reference teeth fixed to the output shaft. The concentric shafts are fixed together at the other end in a cantilever manner. Peripheral teeth are mounted to the outer concentric shaft adjacent and interposed with the reference teeth. A magnetic electrical detector is provided to measure relative displacement between the teeth, and thus the torque magnitude can be determined.
    Type: Grant
    Filed: December 13, 1985
    Date of Patent: July 28, 1987
    Assignee: Pratt & Whitney Canada Inc.
    Inventors: Pierre Morissette, Alexander W. Stewart, Keith H. Taylor
  • LIQUID HYDROGEN EVAPORATORS AND HEATERS
    Publication number: 20230045911
    Abstract: In accordance with at least on aspect of this disclosure, there is provided a hydrogen fuel system for aircraft. The hydrogen fuel system includes a gas turbine engine and a fuel feed conduit. The fuel feed conduit is defined at least in part by, in fluid series, a liquid hydrogen tank fluidly connected to a combustor of the gas turbine engine, a liquid hydrogen pump to drive fuel to the combustor of the gas turbine engine, an evaporator, and an electric heat source in thermal communication with the evaporator to add heat into a flow of hydrogen passing through the evaporator. In embodiments, the electric energy source associated with the electric heat source to power the electric heat source.
    Type: Application
    Filed: August 14, 2021
    Publication date: February 16, 2023
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Scott Smith
  • Gas turbine engine recuperator with floating connection
    Patent number: 9394828
    Abstract: A gas turbine engine recuperator including a plurality of independent arcuate segments, each segment having an inlet connection member designed to sealingly engage a plenum in fluid flow communication with the compressor discharge, and an outlet connection member designed to sealingly engage a plenum containing the combustor. One of the inlet and outlet connection members is a rigid member forming a rigid connection to the respective plenum, and the other of the inlet and outlet connection members includes a flexible member and forms a floating connection to the respective plenum, the floating connection allowing relative movement between the segment and a remainder of the gas turbine engine.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: July 19, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu
  • System and method for purging a fuel manifold of a gas turbine engine using a pump
    Patent number: 11486303
    Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifolds and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and using a pump to drive gas into the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
    Type: Grant
    Filed: May 11, 2020
    Date of Patent: November 1, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Antwan Shenouda
  • Method and system for operating an engine in a multi-engine aircraft
    Patent number: 11168621
    Abstract: Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.
    Type: Grant
    Filed: March 5, 2019
    Date of Patent: November 9, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean McCarthy, Patrick Manoukian, Zachary Mounir Faty, Carmine Lisio, Philippe Beauchesne-Martel
  • System and method for aircraft propeller governing
    Patent number: 11554851
    Abstract: Methods and systems for governing an aircraft propeller of an engine are described. The method comprises obtaining a fluid flow command for speed control of the propeller, determining pulse parameters of a pulse width modulated valve control signal for actuating a two-position solenoid valve in accordance with the fluid flow command based on an average fluid flow through the solenoid valve and an opening and closing time of the solenoid valve, generating the valve control signal with the pulse parameters as determined, and transmitting the valve control signal to the solenoid valve for actuating the solenoid valve, thereby controlling the speed of the propeller.
    Type: Grant
    Filed: February 15, 2019
    Date of Patent: January 17, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gabriel Meunier, Nicolas Des Roches-Dionne
  • Method for manufacturing a composite guide vane having a metallic leading edge
    Patent number: 11680489
    Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.
    Type: Grant
    Filed: May 6, 2022
    Date of Patent: June 20, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Barry Barnett
  • Hybrid electric powerplant (HEP) control architecture
    Patent number: 11649038
    Abstract: A system includes a thermal engine operatively connected to drive a propeller. An electric motor is operatively connected to the thermal engine to drive the propeller together with the thermal engine. An external input system is configured to accept input and output a thrust command. A protection function module is configured to enforce limits on the thermal engine, electric motor, and propeller. A low select module is operatively connected to receive input from the external input system and form the protection function module and to output the lower of input from the protection function module and external input system to the thermal engine, the electric motor, and the propeller.
    Type: Grant
    Filed: July 10, 2020
    Date of Patent: May 16, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Mark, Leonid Guerchkovitch
  • MACHINE TOOL CERTIFICATION FOR PART SPECIFIC WORKING VOLUME
    Publication number: 20150088299
    Abstract: A method for machining a selected part with a machine tool, comprises obtaining a master part replicating at least a portion of a geometry of a selected part. The master part is loaded in a machine tool. A signature of the machine tool is defined by measuring at least dimensional data of the master part relative to the machine tool, the dimensional data being limited to a selected-part-specific working volume substantially smaller than a complete working volume of the machine tool. The machine tool is certified as being within tolerances to machine the selected part within the working volume, using the dimensional data of the signature. The selected part is machined from a workpiece with the machine tool.
    Type: Application
    Filed: September 25, 2013
    Publication date: March 26, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Mario Blais, Philippe St-Jacques
  • Carbon seal assembly
    Patent number: 10107121
    Abstract: A carbon seal assembly comprises an annular member adapted to be secured to a structure. An annular seal runner is sealingly mounted to a shaft to rotate therewith, with the seal runner being made of a material complementary to that of the annular member for magnetic attraction therebetween. An annular carbon seal element is mounted to the annular seal runner to rotate therewith and positioned in a gap between the annular member and the annular seal runner, the annular carbon seal element having an annular wear surface abutting against a face of the annular member. A cross-sectional area of the annular carbon seal element increases as the axial dimension of the annular seal runner decreases for at least a part of the seal.
    Type: Grant
    Filed: December 5, 2012
    Date of Patent: October 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Ivor John Roberts
  • Impeller exducer cavity with flow recirculation
    Patent number: 11268536
    Abstract: A centrifugal compressor for an aircraft engine is disclosed, having an impeller mounted for rotation about an axis. The impeller has impeller blades extending from an inducer end to an exducer end. A shroud extends over the impeller blades. A main flow passage is defined between the shroud and the impeller, a cavity fluidly communicates with the main flow passage via at least one extraction port and at least one reinjection port. The reinjection port is fluidly connected to the main flow passage upstream of the extraction port relative to a flow direction through the main flow passage. The reinjection port is disposed upstream of the exducer end of the impeller blade, in an exducer portion of the shroud.
    Type: Grant
    Filed: September 8, 2020
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hien Duong
  • Gas turbine engine heat management system
    Patent number: 9097169
    Abstract: A heat management system of a gas turbine engine for cooling oil and heating fuel, includes an oil circuit having parallel connected first and second branches. The first branch includes a fuel/oil heat exchanger and a first fixed restrictor in series and the second branch includes an air cooled oil cooler and a second fixed restrictor. The first and second fixed restrictors limit respective oil flows through the first and second branch differently, in response to viscosity changes of the oil caused by temperature changes of the oil during engine operation to modify oil distribution between the first and second branches.
    Type: Grant
    Filed: October 11, 2011
    Date of Patent: August 4, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Adam Logan, Daniel Alecu
  • Rotary internal combustion engine with pilot subchamber and ignition element
    Patent number: 9334794
    Abstract: A rotary engine including an insert in one of the walls of the outer body having a pilot subchamber defined therein communicating with the internal cavity of the engine. An ignition element extends in an element cavity defined through the insert adjacent the subchamber. A portion of the element is in communication with the subchamber through a communication opening defined in the insert between the element cavity and the subchamber. The communication opening has a cross-section smaller than a corresponding cross-section of the portion of the element. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.
    Type: Grant
    Filed: June 5, 2013
    Date of Patent: May 10, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Gaul, André Julien, Bruno Villeneuve
  • CIRCULATING COOLANT FLUID IN HYBRID ELECTRICAL PROPULSION SYSTEMS
    Publication number: 20220185494
    Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor configured to drive a motor shaft. A transmission system is connected to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. A first lubrication/coolant system is connected for circulating a first lubricant/coolant fluid through the heat engine. A second lubricant/coolant system in fluid isolation from the first lubrication/coolant system is connected for circulating a second lubricant/coolant fluid through the electric motor.
    Type: Application
    Filed: December 20, 2021
    Publication date: June 16, 2022
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Jean Dubreuil, Eric LaTulipe
  • Method for manufacturing a composite guide vane having a metallic leading edge
    Patent number: 11352891
    Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.
    Type: Grant
    Filed: October 19, 2020
    Date of Patent: June 7, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Barry Barnett
  • TOWER SHAFT (UTS) SHIELDING
    Publication number: 20080073152
    Abstract: An oil shield for an upper tower shaft gear. The shield provides a plurality of shield members for encapsulating the upper tower shaft gear to reduce the amount of displaced oil from contacting surrounding engine components. The shield includes a first shield member adjacent a top surface of the upper tower shaft gear and a second shield member adjacent an under surface of the upper tower shaft gear which is engaged with the first shield member to enclose the upper tower shaft gear. A third shield member is positioned adjacent the second shield member. The shield members permit oil drainage in a predetermined pattern without undesirable dispersion within the engine compartments.
    Type: Application
    Filed: September 25, 2006
    Publication date: March 27, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas ELEFTHERIOU, David DENIS
  • Method of machining airfoils by disc tools
    Patent number: 7303461
    Abstract: A method for machining a rotor having a disc and a plurality of integral airfoils projecting outwardly from the disc, according to one aspect of the invention, comprises a step of machining each airfoil with a disc tool having a grinding periphery thereof adapted for removing material from the airfoils. The grinding periphery has a thickness greater than a thickness of an adjacent supporting portion of the disc to permit the grinding periphery to pass a surface of an airfoil in a multi-axis simultaneous motion, thereby matching the grinding periphery with a predetermined geometry of a portion of the airfoil.
    Type: Grant
    Filed: December 5, 2006
    Date of Patent: December 4, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Marc Lorenzo Campomanes, Charles Edward Becze, Bastien Ste-Marie
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