Search Patents
  • Multiple zone cooling apparatus
    Patent number: 8784022
    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 23, 2010
    Date of Patent: July 22, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: James Leishman, Fuat Atabey
  • Mistuned fan for gas turbine engine
    Patent number: 10837459
    Abstract: A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: November 17, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Daniel Fudge, Kari Heikurinen, Paul Stone, Ignatius Theratil, Peter Townsend, Tibor Urac
  • Tool assembly and method for removing a component mounted to a carrier
    Patent number: 11883934
    Abstract: A tool assembly is provided for removing a component from a carrier. The component circumscribes and is mounted on the carrier. The tool assembly includes a tool head, an adaptor and an actuator. The tool head is configured to couple to the component. The adaptor extends longitudinally along a centerline between an adaptor first end and an adaptor second end. The adaptor is attachable to the tool head at the adaptor first end by a first quick coupler. The actuator includes a housing and a ram. The housing is attachable to the adaptor at the adaptor second end by a second quick coupler. The ram extends longitudinally along the centerline within the adaptor and the tool head to a ram distal end. The ram distal end is configured to engage the carrier.
    Type: Grant
    Filed: December 27, 2021
    Date of Patent: January 30, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Francois Massicotte, Alexandre Marsan
  • Lubricant filter for a turbine engine
    Patent number: 11680525
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a journal bearing and a filter. The journal bearing has an internal bearing bore. The filter is arranged within the internal bearing bore. The filter includes a tubular filter element and a first end cap. The tubular filter element extends axially along an axis between a first end and a second end. A perforated portion of the tubular filter element is radially disposed away from the journal bearing by a cavity. The first end cap is mounted to the tubular filter element at the first end. The first end cap is sealed radially against the journal bearing by a first interference fit.
    Type: Grant
    Filed: August 20, 2021
    Date of Patent: June 20, 2023
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bruno Martin, Michel Desjardins
  • Fuel nozzle and associated method of assembly
    Patent number: 11486581
    Abstract: The fuel nozzle can have a proximal member having a first mating portion defined around an assembly axis, a first fluid conduit internal to the proximal member and spaced apart from the assembly axis, and a first stop facing a first circumferential direction; and a distal member having a second mating portion configured for axial engagement with the first mating portion along the assembly axis, a second stop facing a second circumferential direction, the second circumferential direction opposite the first circumferential direction and configured to abut against the first stop when the distal member and proximal member are axially engaged to one another in a predetermined relative circumferential alignment.
    Type: Grant
    Filed: September 29, 2020
    Date of Patent: November 1, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Nadia Swaby
  • Wall construction for gaspath traversing component
    Patent number: 10711625
    Abstract: A gaspath traversing component of a gas turbine engine comprises a wall having an outer edge surface and a thickness relative to the gaspath, the wall having a plurality of layers of composite materials forming the thickness. A wear indication layer is embedded within the plurality of layers of composite material, the wear indication layer being visually contrasting with the composite material. The wear indication layer is positioned interiorly of at least one layer of said plurality of layers of composite material relative to the outer edge surface. A method for attending to a gas traversing component of a gas turbine engine is also provided.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: July 14, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Stephen Caulfeild, Kin-Leung Cheung, Mathieu Poulin, Bryan William Olver
  • Gaseous fuel leakage from fuel system manifold to engine
    Patent number: 11767795
    Abstract: There are describes methods and systems for operating an engine coupled to a fuel system having a fuel manifold configured to supply fuel to a combustor of the engine. The method comprises receiving a gaseous fuel flow request indicative of a change in demand for gaseous fuel to the engine; applying a fuel loss bias to the gaseous fuel flow request to obtain a biased fuel flow request, the fuel loss bias associated with a change in mass flow rate of the gaseous fuel from the fuel manifold to the combustor in response to the change in demand; and causing the gaseous fuel to flow into the combustor in accordance with the biased fuel flow request.
    Type: Grant
    Filed: August 19, 2021
    Date of Patent: September 26, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Dillon, Todd Miller
  • Gas turbine engine with bearing support structure
    Patent number: 11391179
    Abstract: The gas turbine engine can have a structure for holding bearings within a casing, with a shaft being rotatably mounted to the casing via the bearings and via the structure, the structure having a first wall segment and a base structure receiving the bearings, the first wall segment having a proximal end structurally joined to the base structure, the first wall segment extending away from the base structure, and having a portion extending at least partially axially and thereby being radially flexible relative to the second wall segment, the structure providing both structural resistance and radial stretchability.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Remy Synnott, François Doyon
  • Gas turbine engine with bearing buffer air flow and method
    Patent number: 9617916
    Abstract: The gas turbine engine has a bleed air aperture formed in the radially outer wall upstream from the combustor and a bearing cavity formed within the radially inner wall, at least two bearing seals enclosing at least one bearing in the bearing cavity and separating the bearing cavity from associated buffer air entry points, an oil supply system including oil paths leading to each of the bearings; a buffer air supply system including buffer air paths leading to each of the entry points and a baffle partitioning one of the entry points.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: April 11, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Pierre-Yves Légaré, Alessandro Ciampa, Michel Labbé
  • OIL FEED ASSEMBLY
    Publication number: 20080073154
    Abstract: An oil feed assembly suitable for use in a gas turbine engine having a bearing housing, an outer ring surrounding the bearing housing and a monocase extending therebetween. The assembly provides an oil supply tube for extension within the monocase and between the outer ring and the bearing housing. An oil nozzle support means is employed for selective releasable engagement with one end of the oil supply tube. This is also supported by an oil supply tube support means for selective releasable engagement with a second end of the oil supply tube. A coupling means for coupling said oil supply tube support means and the outer ring completes the assembly.
    Type: Application
    Filed: September 27, 2006
    Publication date: March 27, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas ELEFTHERIOU, David DENIS, Denis LECLAIR, Julien GARON, Jean FOURNIER
  • Portable test stand for aircraft engines
    Patent number: 11460373
    Abstract: A portable attitude test stand (PATS) for an aircraft engine, has: a support frame mountable on a trailer of a road vehicle; a test cell supported by the support frame and sized to receive the aircraft engine, the test cell operable to rotate the aircraft engine about a pitch axis and a roll axis of the aircraft engine; and an actuator operatively connected to the test cell and to the support frame, the actuator operable to lower and raise the test cell relative to the support frame between a transport configuration in which the test cell has a transport height and a test configuration in which the test cell has a test height, the test height being greater than the transport height.
    Type: Grant
    Filed: September 4, 2020
    Date of Patent: October 4, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Douglas Monahan, Gabor Kafka
  • Small exit duct for a reverse flow combustor with integrated cooling elements
    Patent number: 10527288
    Abstract: The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: January 7, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Robert Sze
  • Integrally bladed fan rotor
    Patent number: 10371162
    Abstract: An integrally bladed fan (IBF) rotor of a gas turbine engine. The IBF rotor includes a hub and a plurality of fan blades extending radially outwardly from the hub and integral therewith. The hub has a fan attachment flange disposed at an end of the hub on a trailing edge side thereof for mounting a booster rotor to a trailing edge side of the fan. The fan attachment flange is disposed at a radial distance from a longitudinal center axis of the integrally bladed fan rotor. The hub has an outer hub surface disposed radially inward from the radial distance of the fan attachment flange.
    Type: Grant
    Filed: October 5, 2016
    Date of Patent: August 6, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, Richard Ivakitch, David Menheere
  • Turbine shroud cooling
    Patent number: 11118475
    Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.
    Type: Grant
    Filed: January 23, 2020
    Date of Patent: September 14, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
  • TANDEM ELECTRIC MACHINE ARRANGEMENT
    Publication number: 20130249338
    Abstract: The tandem electric machine arrangement comprises an outside rotor having two axially spaced-apart sets of circumferentially-disposed permanent magnets. It also comprises an inside stator having at least two electrically-independent windings, the at least two windings axially spaced apart from one another and disposed relative to the magnet sets to thereby be magnet coupled to a respective one of the sets of permanent magnets during rotation of the rotor. One of the rotor and the stator is provided in two separate pieces, each piece supported from opposite axial sides of the electric machine relative to one another. The other of the rotor and the stator is supported from substantially centrally of the two pieces.
    Type: Application
    Filed: May 16, 2013
    Publication date: September 26, 2013
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Kevin Allan DOOLEY, Joseph BRAND
  • Epicyclic gear train of aircraft powerplant
    Patent number: 11598407
    Abstract: An epicyclic gear train of an aircraft powerplant is provided. The epicyclic gear train includes a sun gear having a rotation axis, a ring gear, a plurality of intermediate gears circumscribed by the ring gear and being meshed with the sun gear and with the ring gear, a carrier supporting the intermediate gears, and a torque frame attaching the carrier to a stationary structure of the aircraft powerplant to prevent rotation of the carrier and of the intermediate gears about the rotation axis of the sun gear. The torque frame is attached to the carrier at a connection. The torque frame and the carrier cooperatively define a lubricant passage extending through the connection and supplying lubricant to at least one of the intermediate gears.
    Type: Grant
    Filed: February 16, 2022
    Date of Patent: March 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michel Desjardins
  • Compressor variable vane assembly
    Patent number: 9533485
    Abstract: A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections the inner and/or outer shroud which protruded into the annular gas path such as to ensure that a radial clearance gap, defined between the projections and a vane airfoil overhang portion, remains substantially constant throughout a substantial portion of the vane pivot arc of the variable vane. The method includes forming one cavities within the shroud, the cavities isolated from the annular gas path and disposed radially beneath at least each of the projections, and providing one or more structural reinforcing elements within the cavities.
    Type: Grant
    Filed: March 28, 2014
    Date of Patent: January 3, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andrew R. Marshall, David Menheere
  • Turbine blade airfoil profile
    Patent number: 11572790
    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 11, 2021
    Date of Patent: February 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Remo Marini, Panagiota Tsifourdaris, Nicolas Grivas, Daniel Lecuyer, Michael Papple, Robert Huszar, Othmane Leghzaouni, Jonathan Dorai, Jasrobin Grewal
  • Flat key washer
    Patent number: 6059486
    Abstract: A key washer for interlocking a pair of concentric parts is described. The key washer is comprised of a flat, metal ring having an outer circumferential edge and an inner circumferential edge. Two or more formations are formed in the inner circumferential edge and adapted to be received on a mating formation of an inner one of the concentric parts. The outer circumferential edge has a plurality of straight flat sections for mating engagement with a corresponding configured surface of an outer one of the concentric parts. The metal ring prevents rotation between the concentric parts. The washer is utilized in a preferred application for interlocking an aircraft turbine engine high pressure rotor assembly and a tie shaft nut.
    Type: Grant
    Filed: June 3, 1998
    Date of Patent: May 9, 2000
    Assignee: Pratt & Whitney Canada Inc.
    Inventor: Eric Latulipe
  • Reduction gearbox for aircraft engine
    Patent number: 10400858
    Abstract: A reduction gearbox for an aircraft engine, including an input pinion configured to be driven by the aircraft engine, a input gear meshed with the input pinion, a drive gear meshed with the input gear, an output pinion, and an output gear meshed with the output pinion and configured to drive an output shaft of the aircraft engine. The reduction gearbox is selectively configurable between an engaged configuration where the input gear and output pinion are drivingly engaged and a disengaged configuration where the input gear is rotatable independently of the output pinion. The output shaft may drive a propeller and the gearbox may include a propeller brake. A method of driving a generator of a turboprop engine is also discussed.
    Type: Grant
    Filed: June 9, 2016
    Date of Patent: September 3, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Keith Morgan
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