Search Patents
  • Gas turbine engine rotor assembly and method of using same
    Patent number: 11674394
    Abstract: The rotor assembly can have a first disc having a first body extending circumferentially and radially around the axis, a first set of circumferentially distributed blades protruding radially from the first disc, and a male spline extending axially relative the first body, the male spline extending around and along the axis, and a second disc having a second body extending circumferentially and radially around the axis, a second set of circumferentially distributed blades protruding radially from the second disc, and a female spline extending around and along the axis, the female spline receiving the male spline in a spline engagement.
    Type: Grant
    Filed: February 11, 2021
    Date of Patent: June 13, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Julien Lalonde
  • Turbine blade airfoil profile
    Patent number: 11578602
    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 exterior 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 described 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: October 14, 2021
    Date of Patent: February 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Fariba Ajalli, Panagiota Tsifourdaris, Lorenzo Sanzari, Francis Gemme, Stephane Bigras, William Mindenhall, Masoud Roshan Fekr
  • System and method for detection of excessive flow in a fluid system
    Patent number: 11585272
    Abstract: There is provided a system and method for detecting excess flow in an engine fluid system, the method comprising sensing a temperature of a fluid flowing in a fluid line of the fluid system, the fluid line located downstream of a fluid flow restrictor configured to receive the fluid from a source upstream thereof and to flow the fluid from the source into the fluid line downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line and outputting an excess flow indication accordingly.
    Type: Grant
    Filed: June 25, 2020
    Date of Patent: February 21, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Dana Tomescu, Nick Stina
  • Noise reduction using IGV flow ejections
    Patent number: 10371170
    Abstract: In one embodiment, a method for reducing noise generated by inlet guide vane (IGV) wake and rotor interaction in a turbine engine, the noise having acoustic energy substantially dominating at one or two frequencies, comprises altering noise frequencies to distribute the acoustic energy into a broadband frequency spectrum by ejecting fluid flows from holes located on a side near a trailing edge of at least one of a plurality of inlet guide vanes (IGVs), toward a rotor downstream of the IGVs to merge with an air flow guided by the side of the at least one of the IGVs for interfering with said IGV wake and rotor interaction.
    Type: Grant
    Filed: April 21, 2015
    Date of Patent: August 6, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Hong Yu
  • Combustor liner with improved heat shield retention
    Patent number: 7845174
    Abstract: A combustor liner including a dome section having a positioning hole defined at a first radial distance and sized to receive a first heat shield fastener to at least substantially prevent radial and circumferential motion of the first fastener, a circumferential slot sized to receive a second heat shield fastener to at least substantially prevent radial motion of the second fastener while allowing limited circumferential motion of the second fastener, and a clearance hole defined at a second radial distance and sized to receive a third heat shield fastener to allow limited radial and circumferential motion of the third fastener.
    Type: Grant
    Filed: April 19, 2007
    Date of Patent: December 7, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kenneth Parkman, Stephen Phillips
  • 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
  • COMBUSTION SYSTEM FOR A GAS TURBINE ENGINE AND METHOD OF OPERATING SAME
    Publication number: 20150247641
    Abstract: A gas turbine engine comprises a combustion system comprising a secondary annular combustor and a primary combustor in fluid communication with the secondary combustor, a secondary fuel injector associated with the secondary combustor, a primary fuel injector associated with the primary combustor, and a ECU controlling fuel delivery to the secondary and primary fuel injectors. The primary fuel injector delivers fuel to the primary combustor. The ECU allows fuel to be delivered to the secondary fuel injector in addition to the primary fuel injector only when a fuel amount higher is requested delivered by the primary fuel injector. A method of operating a gas turbine engine is also presented.
    Type: Application
    Filed: February 28, 2014
    Publication date: September 3, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. PATEL, Oleg MORENKO
  • Annular bearing compartment
    Patent number: 5415478
    Abstract: The present invention relates to a bearing compartment for a turbomachine such as a gas turbine engine. The compartment includes a bearing compartment, to which is attached, on its front and rear sides, covers that allow for the passage of air through the compartment as well as past the compartment. In particular, the compartment includes a plurality of axially extending and circumferentially spaced apart sealed air cavities surrounding an oil cavity in the compartment; the bearing which supports a shaft extending through the engine is supported by the bearing. The compartment also includes a plurality of axially extending and circumferentially buffer air cavities surrounding the sealed air cavities, thereby providing additional insulate protection to the oil cavity.
    Type: Grant
    Filed: May 17, 1994
    Date of Patent: May 16, 1995
    Assignee: Pratt & Whitney Canada, Inc.
    Inventors: Anthony J. Matthews, Kenneth D. Parkman
  • Compound cycle engine
    Patent number: 9512721
    Abstract: A compound cycle engine having at least one rotary unit defining an internal combustion engine, a velocity turbine in proximity of each unit, and a turbocharger is discussed. The exhaust port of each rotary unit is in fluid communication with the flowpath of the velocity turbine upstream of its rotor. The rotors of the velocity turbine and of each rotary unit drive a common load. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit, and the inlet of the pressure turbine of the turbocharger is in fluid communication with the flowpath of the velocity turbine downstream of its rotor. A method of compounding at least one rotary engine is also discussed.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: December 6, 2016
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Jean Thomassin
  • Igniter for gas turbine engine
    Patent number: 11268486
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Freer, Kian Mccaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Gas turbine engine heat management system
    Patent number: 10138814
    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: June 25, 2015
    Date of Patent: November 27, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Adam Logan, Daniel Alecu
  • Method and system for non-functional combustion chamber detection
    Patent number: 10823097
    Abstract: Systems and methods for detecting at least one non-functional combustion chamber of an engine comprising a plurality of combustion chambers are described herein. In response to detecting a partial output power loss of the engine, one of the plurality of combustion chambers is assessed by monitoring an engine parameter indicative of an output power of the engine, determining whether a change in the engine parameter has occurred, when the change has occurred, determining that the combustion chamber is functional, and when no change has occurred, determining that the combustion chamber is non-functional and discontinuing fuel injection to the non-functional combustion chamber.
    Type: Grant
    Filed: May 15, 2018
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Lanktree, David Gagnon-Martin, Bruno Villeneuve
  • Hybrid metal/composite link rod for turbofan gas turbine engine
    Patent number: 9068476
    Abstract: The link rod can have a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape, the strut body being secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing mountable to the core portion, and the cold end housing a spherical bearing mountable to the bypass duct wall.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: June 30, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Stephen Caulfeild, Bryan Olver
  • Multiple zone cooling apparatus
    Patent number: 9033626
    Abstract: A cooling assembly for a machine tool including at least first and second nozzle rings mounted on the spindle housing, respectively defining first and second coolant conduits and respectively including first and second pluralities of nozzles in fluid communication with the respective conduit. Each first nozzle is oriented with an outlet thereof directed toward a first machining zone containing cutting edges of at last one tool having a first length. Each second nozzle is oriented with an outlet thereof directed toward a second machining zone different from the first machining zone and containing the cutting edges of at least one tool having a second length.
    Type: Grant
    Filed: June 12, 2014
    Date of Patent: May 19, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: James Leishman, Fuat Atabey
  • Labyrinth seal with angled fins
    Patent number: 11293295
    Abstract: An aircraft engine having a shaft, an engine casing, at least one bearing located between the shaft and the engine casing, the engine casing defining a bearing cavity containing the at least one bearing, an air distribution system configured to inject compressed air to the bearing cavity to in use provide a sealing air flow entering the bearing cavity, and a labyrinth seal having a seal rotor and a seal stator, fins extending from one of the seal rotor and the seal stator toward the other of the seal rotor and the seal stator, at least one of the fins extending in an angled upstream direction relative to a direction of the sealing air flow.
    Type: Grant
    Filed: September 13, 2019
    Date of Patent: April 5, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Alexander Smith, Pierre-Yves Legare
  • Combustor with chamfered dome
    Patent number: 8171736
    Abstract: A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a dome end portion of the shell, at least the outer flange including intersecting upstream and downstream wall portions defining a corner therebetween, the upstream wall portion having a plurality of cooling apertures defined therethrough immediately upstream of the corner, and the cooling apertures being oriented to direct a cooling air flow from outside the combustor shell therethrough and adjacent an inner surface of the downstream wall portion.
    Type: Grant
    Filed: January 30, 2007
    Date of Patent: May 8, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eduardo Hawie, Robert Sze
  • Assist system and method for aircraft ground operation
    Patent number: 11772820
    Abstract: An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.
    Type: Grant
    Filed: May 27, 2021
    Date of Patent: October 3, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Daniel Alecu
  • Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs
    Patent number: 8635875
    Abstract: A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes. The outer lobes protrude into the annular bypass passage of the engine, whereas the inner lobes protrude into the main gas path passage of the engine. The inner and outer lobes respectively define alternating troughs and crest with radial interconnecting walls therebetween. The mixer has a jagged trailing edge including a plurality of tabs extending from each radial wall between the troughs and the crests.
    Type: Grant
    Filed: April 29, 2010
    Date of Patent: January 28, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Mark Huzzard Cunningham
  • Gas turbine engine shaft architecture and associated method of disassembly
    Patent number: 10393027
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: August 27, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, John Pietrobon
  • Thermal and external load isolating impeller shroud
    Patent number: 7908869
    Abstract: A gas turbine engine has a compressor assembly and a turbine assembly rotationally mounted on a shaft, the turbine assembly being driven by hot gases discharged from a combustion chamber disposed between the compressor and turbine assemblies, the compressor having a centrifugal impeller for pressurizing and impelling air into the combustion chamber. The engine also includes an impeller shroud covering the bladed portion of the centrifugal impeller, the impeller shroud having a support bracket having a thin and curved load-isolating profile for supporting a strut that secures the impeller shroud to a case of the engine.
    Type: Grant
    Filed: September 18, 2006
    Date of Patent: March 22, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Richard Ivakitch, Philip Ridyard, Patrick Chiu
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