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  • Carrier journal with anti-rotation feature
    Patent number: 11149786
    Abstract: A journal bearing assembly for rotatably supporting a gear in a gear system. The journal bearing assembly comprises a journal bearing for rotatably supporting the at least one gear. The journal bearing includes an engagement feature at a distal end thereof. The distal end is insertable into an opening in a gear carrier of the gear system. The opening includes an anti-rotation feature engageable with the engagement feature to block the journal bearing from rotating about an axis extending longitudinally through the center of the journal bearing. The journal bearing assembly further includes a fastening feature for fastening the journal bearing to the gear carrier.
    Type: Grant
    Filed: February 28, 2020
    Date of Patent: October 19, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Bruno Martin
  • Method of apex seal lubrication for a rotary internal combustion engine
    Patent number: 11008909
    Abstract: A rotary internal combustion engine with a housing having a fluid passage defined therethrough opening into a portion of its inner surface engaging each peripheral or apex seal of the rotor. An injector has an inlet for fluid communication with a pressurized lubricant source and a selectively openable and closable outlet in fluid communication with the fluid passage for delivering the pressurized lubricant to each seal through the fluid passage. A housing for a Wankel engine and a method of lubricating peripheral seals of a rotor in an internal combustion engine are also discussed.
    Type: Grant
    Filed: January 23, 2020
    Date of Patent: May 18, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Edwin Schulz, Etienne Plamondon, Jean Thomassin
  • Method and system for preventing un-commanded power surge of aircraft engine
    Publication number: 20040088085
    Abstract: A method of preventing un-commanded power surging of an aircraft engine includes two steps of detecting whether the Weight-On-Wheels signal is on and detecting whether the Low-Power-Lever-Angle-Discrete signal is on, which indicate whether the aircraft is on the ground and whether the throttle lever is positioned for a low power range. If both results are positive, a further step is performed for comparing a measured engine power or thrust level with a predetermined threshold and a final step reduces the fuel supply or shuts down the engine, if the measured engine power level is greater than the predetermined threshold.
    Type: Application
    Filed: October 30, 2002
    Publication date: May 6, 2004
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Antonio Hernani Nobre
  • Exhaust duct of gas turbine engine
    Patent number: 11286814
    Abstract: An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.
    Type: Grant
    Filed: September 17, 2020
    Date of Patent: March 29, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Rabih Kassab
  • Method for regulating fuel flow in a gas turbine engine
    Patent number: 5329759
    Abstract: Fuel flow to the combustor of a gas turbine engine is regulated by controlling the amount of fuel delivered to the primary and secondary fuel orifices of a hybrid fuel nozzle. A one-way valve extending between primary and secondary fuel manifolds is controlled by an electronic sensor that acts upon signals received from sensors at station 4.5 of the engine, and by sensors that measure engine speed. By opening and closing the valve based upon T.sub.4.5 and N.sub.2 speed, optimum engine operating conditions are achieved.
    Type: Grant
    Filed: June 30, 1993
    Date of Patent: July 19, 1994
    Assignee: Pratt & Whitney Canada, Inc.
    Inventor: Hing C. Chan
  • Diffuser pipe with non-axisymmetric end wall
    Patent number: 10823195
    Abstract: A compressor diffuser for a gas turbine engine comprises a plurality of diffuser pipes having a tubular body. The pipes have a first portion having a radial component and defining a throat at a location along the first portion, a second portion having an axial component, and a curved portion fluidly linking the first portion and the second portion. The first portion has an inner surface with a local surface contour located between the throat and the curved portion. The local surface contour extends along a portion of and around less than an entire perimeter of the first portion.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hien Duong
  • Mounting system for mounting engine nacelle components and associated method
    Patent number: 8979020
    Abstract: The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connecting the engine structure to the pylon, and a flexible connection provided between the hinged connections and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position.
    Type: Grant
    Filed: June 7, 2013
    Date of Patent: March 17, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ovidiu Badescu, Antonio Pizzi
  • Method for applying a coating to a substrate
    Patent number: 9347136
    Abstract: A method for applying a coating to a substrate surface is provided. The method involves cold spraying a coating material against the surface of the substrate at a first velocity. The first velocity is lower in magnitude than a critical velocity. The method also involves cold spraying the coating material against the surface of the substrate at a second velocity. The second velocity is greater in magnitude than the critical velocity. The critical velocity is a threshold velocity below which the coating material is substantially deflected by the surface of the substrate and above which the coating material substantially adheres to the surface of the substrate.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: May 24, 2016
    Assignees: PRATT & WHITNEY CANADA CORP., NATIONAL RESEARCH COUNCIL OF CANADA
    Inventors: Pierre Verrier, Eric Irissou, Frederic Belval, Jean-Gabriel Legoux
  • Compressor airfoil
    Patent number: 9732762
    Abstract: A compressor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip of the airfoil. A leading edge sweep angle is defined relative to a tangent to the airfoil and flow velocity vector at a point on the leading edge. A leading edge dihedral angle is defined relative to the tangent to the airfoil and a vertical at the point on the leading edge. A ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1. A method of forming such airfoil is also presented.
    Type: Grant
    Filed: August 27, 2014
    Date of Patent: August 15, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Jason Nichols
  • Blade containment assembly for a gas turbine engine
    Patent number: 11530622
    Abstract: A blade containment assembly for a gas turbine engine comprises a casing having a first casing member surrounding a set of rotor blades and a second casing member extending axially from the first casing member. The first casing member has an outer annular wall welded to the second casing member at a weld joint disposed in a blade containment zone of the casing and an inner containment ring spaced radially inwardly from the outer annular wall and extending axially from a first location forward of the weld joint to a second location aft of the weld joint.
    Type: Grant
    Filed: October 16, 2020
    Date of Patent: December 20, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Francois Doyon
  • Method and system for synchronizing generators
    Patent number: 10224848
    Abstract: There are described methods and systems for synchronizing at least two generators for an engine. A first generator is mechanically coupled to the engine. A power source is connected in parallel to the first generator and to a second generator, the second generator mechanically uncoupled from the engine, the power source connected across a same respective phase of a stator in the first generator and the second generator. Power from the power source is applied to the first generator and the second generator to align a respective rotor to the respective phase in each generator and cause the first generator and the second generator to be in-phase. The second generator is then mechanically coupled to the engine.
    Type: Grant
    Filed: January 30, 2017
    Date of Patent: March 5, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Daniel Alecu
  • Method and apparatus for manufacturing compliant brush seals
    Patent number: 4989919
    Abstract: A method and fixture (10) for assembling compliant seals (30) includes an aligning member (12) having a grooved surface (14) for receiving a plurality of loose bristle elements (16). The bristle elements (16) are received within the grooves (26) and aligned thereby. First and second backing rings (20, 22) sandwich the aligned bristles (16) and are clamped by first and second clamping members (18, 24). The clamped rings (20, 22) and bristle elements (16) are then removed from the aligning member (12) and permanently secured together, forming the finished seal (30).
    Type: Grant
    Filed: August 14, 1989
    Date of Patent: February 5, 1991
    Assignee: Pratt & Whitney Canada
    Inventor: John Greer
  • Grommeted bypass duct penetration
    Patent number: 6942452
    Abstract: A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and the external surface of a projection extending through the opening, where the grommet has an annular body with a central aperture having an interior periphery adapted to sealingly engage the external surface of the projection. A first flange and second flanges define an external slot about an exterior periphery of the body adapted to receive and seal the bypass duct wall between the flanges.
    Type: Grant
    Filed: December 17, 2002
    Date of Patent: September 13, 2005
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Vittorio Bruno, Goli Hadi, Bryan Olver
  • Multiple cutter pass flank milling
    Patent number: 4596501
    Abstract: A method of flank milling complex surfaces comprising the steps of analyzing the design surface to determine discrete areas in which straight lines can be drawn, determining straight lines in the discrete areas, transposing the coordinates of these straight lines and comparing them with the flank tool cutter positions, determining the tool positions to said straight lines, back generating the contact lines of said surface and comparing these with the design surface, determining the number of passes of said cutter tool and generating data for numerical control machining.
    Type: Grant
    Filed: February 24, 1984
    Date of Patent: June 24, 1986
    Assignee: Pratt & Whitney Canada Inc.
    Inventor: Chung Y. Wu
  • Turbine blade airfoil profile
    Patent number: 11603763
    Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
    Type: Grant
    Filed: November 12, 2021
    Date of Patent: March 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Abdulhalim Twahir, Panagiota Tsifourdaris, Niloofar Moradi, Daniel Lecuyer, Jocelyn Menard
  • Multiple aircraft engine control system and method of communicating data therein
    Patent number: 9382011
    Abstract: The multiple aircraft engine control system having a corresponding engine controller associated with each one of the engines, each one of the engine controllers having at least two independent channels, each one of the at least two independent channels having at least two communication buses, each one of the at least two communicating buses of each channel being connected to a respective one of the at least two communicating buses of each one of the other channels. The method can time-interweave originating data of the channels.
    Type: Grant
    Filed: April 10, 2014
    Date of Patent: July 5, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Darby, Brant Duke
  • Diffuser pipe with splitter vane
    Patent number: 10570925
    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.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: February 25, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Vijay Kandasamy, Koundinya Upadrasta
  • Turbine blade airfoil profile
    Patent number: 11867081
    Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
    Type: Grant
    Filed: January 26, 2023
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Abdulhalim Twahir, Panagiota Tsifourdaris, Daniel Lecuyer, Masoud Roshan Fekr, Stephane Bigras
  • Fuel systems and methods for purging
    Patent number: 11808219
    Abstract: A fuel system can include a first fuel circuit, a second fuel circuit, and an inert gas purge system operatively connected to both the first fuel circuit and the second fuel circuit to purge at least a portion of either or both of the first and/or second fuel circuit. The first fuel can be a liquid fuel and the second fuel can be a gaseous fuel. The first fuel circuit can include a first fuel manifold configured to fluidly communicate a first fuel supply with at least one dual fuel nozzles downstream of the first fuel manifold.
    Type: Grant
    Filed: April 12, 2021
    Date of Patent: November 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Owen Ho-Yin Wong, John Galas, Sean Durand
  • Fuel delivery system with reduced heat transfer to fuel manifold seal
    Patent number: 8393154
    Abstract: A gas turbine engine fuel supply assembly which includes a fuel manifold mounted to a casing surrounding a combustor of the engine, and a plurality of fuel nozzles mounted to the fuel manifold. A mating interface between the fuel nozzles and the fuel manifold has at least one sealing element, and at least one aperture defined in the fuel nozzle proximate to the mating interface. The aperture is a non fuel conveying passage, and reduces conductive heat transfer to the sealing element by preventing a direct conductive heat transfer path between a hot region of the fuel nozzle and the sealing element.
    Type: Grant
    Filed: February 12, 2009
    Date of Patent: March 12, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Victor Gandza
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