Search Patents
  • Modulated cooled P3 air for impeller
    Patent number: 10767562
    Abstract: A method and apparatus using a cooler to selectively cool P3 air directed into an impeller rear cavity of a gas turbine engine during engine high power levels, may include connection of the cooler to a low pressure compressor bleed-off valve apparatus that is modulated to be closed during engine high power levels to create a pressure differential over the bleed-off valve apparatus, to drive a stream of low pressure compressor air as a cooling work fluid under such pressure differential to selectively flow through the cooler.
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: September 8, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Xiaoliu Liu
  • Igniter for gas turbine engine
    Patent number: 11268447
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.
    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
  • Spline alignment
    Patent number: 10302140
    Abstract: A gas turbine shaft assembly comprises first and second axially mating shafts. The first shaft has a circumferential array of splines configured to mesh with a corresponding circumferential array of splines on the second shaft. The first shaft defines at least one axially extending slot aligned with one of the splines on the first shaft. The second shaft has at least one radial projection aligned with one of the splines on the second shaft. The engagement of the radial projection with the slot provides angular correspondence between the splines of the first and the second shafts prior to axial engagement of the splines.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: May 28, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Johnny Vinski, Eric Durocher
  • Fuel nozzle
    Patent number: 9822980
    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a plurality of concentrically-arranged nozzle tip projections disposed at a downstream portion of the body. Each of the plurality of nozzle tip projections has a radially inwardly facing fuel filming surface communicating with respective fuel passages. The fuel filming surfaces are disposed radially outwardly of an outlet of the primary air passageway. A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine is also presented.
    Type: Grant
    Filed: September 24, 2014
    Date of Patent: November 21, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eduardo Hawie, Nigel Davenport, Yen-Wen Wang
  • Low-cost frangible cable for gas turbine engine
    Patent number: 7581377
    Abstract: An emergency fuel shut-off system for a gas turbine engine comprises a fuel shut-off device to be actuated for terminating a fuel supply to the engine in response to a mechanical actuation force and an actuator adapted for creating the mechanical actuation force when a rotor shaft of the engine fails. A fuse apparatus is provided to link the actuator with the shut-off device in order to transmit the mechanical actuation force. The fuse apparatus disables transmission of the mechanical actuation force when the transmitted mechanical actuation force exceeds a pre-selected level.
    Type: Grant
    Filed: June 14, 2006
    Date of Patent: September 1, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Robert A. Daukant
  • Igniter for gas turbine engine
    Patent number: 11692489
    Abstract: A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.
    Type: Grant
    Filed: January 26, 2022
    Date of Patent: July 4, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Method and system for failure prediction using lubricating fluid analysis
    Patent number: 10627376
    Abstract: Methods and systems for failure prediction using analysis of oil or other lubricant. Raw data about feature(s) of each of a plurality of particles filtered from a fluid sample are used to categorize each particle into one of a plurality of categories, each category being defined by one or more of: chemical composition, size and morphology. Particle physical characteristics in each category are quantified to obtain a set of categorized data. The categorized data are compared with historical data. Results of the comparing are evaluated to generate a prediction of any failure or mechanism of failure.
    Type: Grant
    Filed: January 16, 2018
    Date of Patent: April 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Maurice Jean, Daniel Meilleur
  • MULTI-PHASE CABLE
    Publication number: 20140144671
    Abstract: A multi-phase cable, the cable including a plurality of conductors for conducting currents of two or more different phases, each phase being associated with one or more conductors and each conductor being associated with one respective phase. Each conductor has a cross-section with at least one dimension that is sized to decrease a skin effect of the conductor at a maximum or nominal operation frequency of the conductor. The conductors are arranged to permit free air cooling of the cable on at least two sides of each conductor, and such that each conductor of a given phase has, as immediate neighbors, only conductors of one or more different phases.
    Type: Application
    Filed: November 27, 2012
    Publication date: May 29, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Antwan SHENOUDA
  • In flight restart system and method for free turbine engine
    Patent number: 10094293
    Abstract: There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.
    Type: Grant
    Filed: August 22, 2014
    Date of Patent: October 9, 2018
    Assignees: PRATT & WHITNEY CANADA CORP., HAMILTON SUNDSTRAND CORPORATION
    Inventors: Robert H. Perkinson, Richard Ullyott
  • Gas turbine engine exhaust case
    Patent number: 11572793
    Abstract: The turbine exhaust case can have an outer shroud, an inner shroud internal to the outer shroud, an annular exhaust path between the outer shroud and the inner shroud, and a plurality of struts each having a length extending across the annular exhaust path from a radially inner end to a radially outer end, the struts circumferentially interspaced from one another, the struts each having a leading edge and a trailing edge, a stiff connection between the radially inner end and the inner shroud, and a point connection between the radially outer end and the outer shroud.
    Type: Grant
    Filed: July 29, 2019
    Date of Patent: February 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Rabih Kassab
  • Dual pre-load cylindrical seal
    Patent number: 9752679
    Abstract: A cylindrical seal apparatus according to one embodiment includes a split spring ring and a split seal ring supported in a groove for example defined in a piston. The split spring ring in a tensioning condition presses against a tapered annular inner surface of the split seal ring to create a radial pre-load and an axial pre-load to the slit seal ring to establish a primary sealing contact between the seal ring and a cylinder, and a second sealing condition between the seal ring and a lower-pressure side of the groove, before the working fluid pressure is built up.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: September 5, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tibor Urac, Bernard Chow
  • Normally open reverse flow flapper valve
    Publication number: 20040118105
    Abstract: A fluid flow actuated valve for controlling the fluid flow in a conduit comprises a support structure adapted to be mounted within the conduit and at least one flap member pivotally mounted to the support structure. The at least one flap member is pivotable between an first position for a minimum fluid flow and a second position for a maximum fluid flow. A torsion spring is attached to the at least one flap member to urge the same to pivot against a fluid pressure differential, from the first position to the second position when the fluid pressure differential is smaller than a predetermined level.
    Type: Application
    Filed: December 18, 2002
    Publication date: June 24, 2004
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Paul Archibald Aitchison, Patrick David Germain, Henry Smith
  • Method and kit for preserving a fuel system of an aircraft engine
    Patent number: 10287909
    Abstract: A method and kit for preserving a fuel system of an aircraft engine outside of an engine test cell in preparation for a period of inactivity of the aircraft engine are disclosed. The method comprises: supplying preservation fluid to the fuel system of the aircraft engine; generating a signal to cause the opening of a valve of the fuel system using a control device other than the electronic engine controller of the aircraft engine; and driving a fuel pump of the fuel system to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: May 14, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Alain Girard
  • System and method for validating component integrity in an engine
    Patent number: 11703421
    Abstract: Methods and systems for validating component integrity in an engine are described. First usage data associated with a period of operation of the engine is obtained at an engine controller. An indication of the first usage data is transmitted from the engine controller to a first presentation device. Second usage data associated with the period of operation of the engine is received at the engine controller from an input device. The first usage data is compared to the second usage data at the engine controller. Based on the comparing, an alert is issued to a second presentation device independent from the first presentation device.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: July 18, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tatjana Pekovic, Sean McCarthy, Andrew Ghattas
  • Exhaust duct and tail cone attachment of aircraft engines
    Patent number: 7950236
    Abstract: An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer case includes a connection apparatus for supportably connecting the exhaust duct to the gas turbine engine and the inner case includes an axial end portion at a rear end thereof for connection with a tail cone. The axial end portion bends radially and inwardly at a rear extremity thereof to stiffen the rear end of the inner ease.
    Type: Grant
    Filed: September 11, 2006
    Date of Patent: May 31, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Rotary internal combustion engine with pilot subchamber
    Patent number: 9353680
    Abstract: A rotary engine with an outer body having an insert located in the peripheral offset from the rotor cavity such that a portion of the peripheral wall extends between the insert and the cavity. The insert has a pilot subchamber defined therein and the portion of the peripheral wall has at least one opening defined therethrough in communication with the at least one outlet opening of the insert and with the cavity. A method of combusting fuel into a rotary engine is also discussed.
    Type: Grant
    Filed: March 4, 2013
    Date of Patent: May 31, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruno Villeneuve, Jean-Gabriel Gauvreau, David Gagnon-Martin, André Julien, Jean Thomassin
  • Cable connection for a gas turbine engine safety fuel shut-off mechanism
    Patent number: 7703270
    Abstract: A mistake proof cable assembly for promoting short time engine assembly and method of assembling same. The mistake proof cable assembly comprises a slotted member defining a slot having an open end, and a cable connected to the slotted member and extending longitudinally through the slot. First and second restrainers are mounted on the cable on opposite sides of the slotted member for limiting free movement of the cable in the longitudinal direction of the slotted member. A lock prevents removal of the cable from the slot through the open end thereof.
    Type: Grant
    Filed: July 15, 2005
    Date of Patent: April 27, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Guy Lefebvre, Eric Durocher
  • Corrected parameters control logic for variable geometry mechanisms
    Patent number: 10961919
    Abstract: Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: March 30, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Philippe Beauchesne-Martel, Poi Loon Tang, Andrew Thompson, Ghislain Plante
  • Detection of uncommanded and uncontrollable high thrust events
    Patent number: 10302021
    Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, comparing an engine fan speed to a reference target and detecting a first condition when a first threshold is exceeded, comparing a rate of change of a high pressure rotor speed to a reference deceleration schedule and detecting a second condition when a second threshold is exceeded, detecting a UHT event based on excess thrust when the first condition and the second condition are detected, and accommodating the UHT event.
    Type: Grant
    Filed: May 3, 2017
    Date of Patent: May 28, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Krynski, Poi Loon Tang, David Mathews, Antwan Shenouda, Yusuf Syed
  • OIL PURGE SYSTEM FOR A MID TURBINE FRAME
    Publication number: 20130189071
    Abstract: An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF.
    Type: Application
    Filed: January 24, 2012
    Publication date: July 25, 2013
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Durocher, John Pietrobon, Zenon Szlanta
Narrow Results

Filter by US Classification