Search Patents
  • Shared oil system arrangement for an engine component and a generator
    Patent number: 10544717
    Abstract: A method of distributing oil to a component within a gas turbine engine includes directing a first oil flow from an oil source to an engine component and back to the oil source, directing a second oil flow from the oil source to a generator driven by the engine and back to the oil source, monitoring a parameter of the second oil flow downstream of the generator and upstream of the oil source, detecting a contaminant in the second oil flow based on the parameter, and reducing the second oil flow to the generator when the contaminant is detected without reducing the first oil flow to the engine component. A shared oil system for a component of a gas turbine engine and a generator driven by the gas turbine engine is also discussed.
    Type: Grant
    Filed: January 30, 2017
    Date of Patent: January 28, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Waddleton, Daniel Matthew McGuire
  • Diffuser with enhanced surge margin
    Patent number: 8235648
    Abstract: A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed angled passages in communication with an inlet space. Each vane includes a bleed port defined in a suction surface thereof, in proximity of the leading edge. The diffuser case includes a passive fluid communication defined at least partially through each one of the vanes between each bleed port and the inlet space upstream of the leading edge, such that air bled through the bleed ports is recirculated upstream of the leading edges to the inlet space to increase a surge margin of the diffuser.
    Type: Grant
    Filed: September 26, 2008
    Date of Patent: August 7, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Andre LeBlanc
  • Method and system for controlling thrust of an engine
    Patent number: 10946972
    Abstract: Systems and methods for controlling thrust of an engine for an aircraft are described herein. A position of a thrust lever for controlling the engine is obtained from one or more sensors. Air data is obtained from one or more air data inputs. An air temperature data input is detected as compromised from the air data. In response to detecting the air temperature data input is compromised, a target engine rotational speed is determined based on the position of the thrust lever and at least one of altitude data and Mach number data from the air data. A rotational speed of the engine is adjusted to the target engine rotational speed to control thrust of the engine.
    Type: Grant
    Filed: November 21, 2018
    Date of Patent: March 16, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Glenn Birch, Faran Hafeez, Regina Parker, Jason Tremblay, Paul Fisher, Michael Krynski, Eric Brossard
  • COMPRESSOR VARIABLE VANE ASSEMBLY
    Publication number: 20150176418
    Abstract: A variable vane assembly for a gas turbine engine compressor with a plurality of pivoting variable vanes extending between inner and outer shrouds and having an overhang portion that protrudes from a button at opposed ends of the vane. A plurality of projections, disposed on at least one of the inner and outer shrouds, protrude into the gas path relative to a nominal gas path boundary of the shrouds. The projections are disposed adjacent the overhang portion and have an angled planar surface that is substantially parallel to a plane swept by a terminal edge of the overhang portion when the variable vane is rotated through its vane pivot arc, so that a radial clearance gap between the shroud and the overhang portion remains substantially constant through a substantial portion of the vane pivot arc.
    Type: Application
    Filed: December 19, 2013
    Publication date: June 25, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Andrew R. Marshall
  • Buffer heat exchangers for hydrogen engines
    Patent number: 11994068
    Abstract: In accordance with at least one aspect of this disclosure, there is provided a heat exchange system. The heat exchange system includes a first heat exchanger and a second heat exchanger. The first heat exchanger includes an engine fluid conduit fluidly connecting an engine fluid inlet to an engine fluid outlet. A first internal buffer fluid conduit fluidly connects a first buffer fluid inlet to a first buffer fluid outlet where the engine fluid conduit is in fluid isolation from the first internal buffer fluid conduit but is in thermal communication with the first internal buffer fluid conduit for heat exchange between the engine fluid and the buffer fluid.
    Type: Grant
    Filed: August 9, 2021
    Date of Patent: May 28, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Scott Smith, Eric Durocher
  • Lubrication system of aircraft engine
    Patent number: 11788433
    Abstract: Lubrication systems of an aircraft engine and associated methods are provided. The lubrication system includes a chamber having a fluid inlet for receiving lubricating fluid into the chamber, and a fluid outlet for draining the lubricating fluid from the chamber. The fluid outlet is disposed on a wall defining part of the chamber. A rotor is disposed inside the chamber and interacts with the lubricating fluid inside the chamber. The rotor is rotatable in a rotation direction about a rotation axis. A perforated baffle is disposed in the chamber for interacting with the lubricating fluid inside the chamber. The perforated baffle includes a base attached to the wall of the chamber. The base of the perforated baffle is disposed at an angular position preceding the fluid outlet relative to the rotation direction of the rotor.
    Type: Grant
    Filed: October 26, 2021
    Date of Patent: October 17, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kenneth Parkman, Daniel Alecu
  • Simultaneously disassembling rotor blades from a gas turbine engine rotor disk
    Patent number: 12000301
    Abstract: A method is provided for disassembling a rotor of a gas turbine engine. During this method, the rotor is provided which includes a rotor disk and a plurality of rotor blades arranged circumferentially about an axis. The rotor blades include a plurality of airfoils and a plurality of attachments that mount the rotor blades to the rotor disk. Each of the rotor blades includes a respective one of the airfoils and a respective one of the attachments. A press is arranged against the rotor. The press axially engages each of the rotor blades. The press moves axially along the axis to simultaneously push the rotor blades and remove the attachments from a plurality of slots in the rotor disk.
    Type: Grant
    Filed: August 19, 2022
    Date of Patent: June 4, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Robert West, Howard Mah, Sowriraja Krishnasamy, Dean-Andrew Michalagas
  • Method of using backflow from common-rail fuel injector
    Patent number: 10865728
    Abstract: There is disclosed a method of operating an engine assembly including a combustion engine and a common-rail injector. The method includes: injecting fuel into a combustion chamber of the combustion engine via the common-rail injector thereby generating a backflow of fuel; and powering an actuator using at least a portion of the backflow of fuel. An engine assembly including the combustion engine is disclosed; the engine assembly having a fuel circuit fluidly connecting a fuel source, the common-rail injector, and the second injector outlet together. The fuel circuit has an actuator sub-circuit operatively connected to an outlet of the common-rail injector and an actuator fluidly connected to the actuator sub-circuit.
    Type: Grant
    Filed: March 13, 2019
    Date of Patent: December 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Etienne Plamondon, Sebastien Bergeron, Benjamin Renaud, Jean-Gabriel Gauvreau
  • Passively orientable pressure probe
    Patent number: 11692455
    Abstract: An aircraft engine, has: a pressure probe having: a static member having a front face and a back face, an inlet and an outlet fluidly connected to the inlet, the front face defining a curved surface; a movable member movably engaged to the static member and movable relative to the static member about a center of rotation, the movable member having a central axis, the movable member having an engagement section matingly engaged to the front face to slide against the curved surface, the engagement section having an opening, and an orientation section protruding from the engagement section and located rearward of the center of rotation, the orientation section defining an external surface exposed to the flow, wherein the movable member is movable relative to the static member as a result of a force imparted by the flow on the external surface.
    Type: Grant
    Filed: September 19, 2022
    Date of Patent: July 4, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Frederic Doucet
  • Secondary air system with venturi
    Patent number: 10100730
    Abstract: A gas turbine engine including a secondary air system with interconnected fluid passages defining at least one flow path between a common source of pressurized air and a common outlet. Some of the fluid passages deliver the pressurized air to components of the gas turbine engine. The fluid passages include a common fluid passage through which all circulation of the pressurized air to the common outlet passes. The common fluid passage has a section including a venturi configured for controlling a flow of the pressurized air from the source to the outlet. In one embodiment, the venturi is provided in a common inlet or common outlet passage. A method of pressurizing a secondary air system is also discussed.
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: October 16, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Roger Huppe, Pierre-Yves Legare
  • Simultaneously assembling rotor blades from a gas turbine engine rotor disk
    Patent number: 11808164
    Abstract: A method is provided for assembling a rotor of a gas turbine engine. During this method, a rotor disk is provided that includes an axis and a plurality of slots arranged circumferentially about the axis in an array. A plurality of rotor blades are provided that include a plurality of airfoils and a plurality of attachments. Each of the rotor blades includes a respective one of the airfoils and a respective one of the attachments. Each of the attachments is inserted partially into a respective one of the slots. The rotor blades are rested on top of a blade support structure. The blade support structure is lowered axially downward along the rotor disk to simultaneously seat the attachments into the slots.
    Type: Grant
    Filed: August 19, 2022
    Date of Patent: November 7, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Robert West, Howard Mah, Sowriraja Krishnasamy, Dean-Andrew Michalagas
  • Connection for generator in a gas turbine engine
    Patent number: 9169780
    Abstract: A gas turbine engine having an electric generator includes a transmission shaft extending along a longitudinal axis of the engine and drivingly interconnecting a turbine shaft of the engine and a rotor shaft of the electric generator. The transmission shaft is engaged by splined mating connections with the turbine shaft and the rotor shaft. The transmission shaft has a shear neck defining a reduced radial wall thickness with respect to a remainder of the transmission shaft such as to provide a weakened region of the transmission shaft. An annular support structure, concentric with and surrounding the transmission shaft, is axially located between the shear neck and a forward end of the transmission shaft engaged to the turbine shaft, and includes a bearing operable to rotationally support the transmission shaft.
    Type: Grant
    Filed: July 15, 2011
    Date of Patent: October 27, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Barry Barnett, Daniel Alecu, Andreas Eleftheriou
  • COMPRESSOR STATOR
    Publication number: 20140271158
    Abstract: Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Yau-Wai LI, Karan ANAND, Peter TOWNSEND
  • Gas turbine with magnetic shaft forming part of a generator/motor assembly
    Patent number: 8097972
    Abstract: A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine engine, an electrical assembly having a rotor comprising permanent magnets retained on an outer surface of the reduced diameter portion and a stator comprising a magnetic field circuit disposed adjacent an outer periphery of the rotor, and an electrical connection between the magnetic field circuit and at least one of a power source and an electrically drivable accessory.
    Type: Grant
    Filed: June 29, 2009
    Date of Patent: January 17, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Enzo Macchia
  • Internal manifold with fuel inlet
    Patent number: 9797313
    Abstract: An internal fuel manifold assembly includes a fuel manifold ring having at least one fuel conveying passage in fluid flow communication with at least one inlet passage defined through an inlet member. The inlet member is connected to the manifold ring proximate its first end and connected proximate its second end to at least one transfer tube. The inlet member includes a drainage passage for collecting possible leaked fuel from an annulus, defined between the inlet member and a heat shield surrounding the inlet member and spaced apart therefrom. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: January 16, 2014
    Date of Patent: October 24, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Air inlet system for auxiliary power units
    Patent number: 10865711
    Abstract: An air inlet system for an auxiliary power unit (APU) has an intake duct having a wall defining an inlet plenum and forming an inlet opening configured to direct air into the inlet plenum. The system further comprising a load compressor passage in fluid communication with the inlet plenum and leading to a load compressor of the APU; and a core compressor passage in fluid communication with the inlet plenum and leading to a core compressor of the APU. A deflector is provided in the inlet plenum between the inlet opening and the core compressor inlet to deflect at least part of particles carried by an incoming airflow away from the core compressor inlet toward the load compressor inlet.
    Type: Grant
    Filed: August 3, 2018
    Date of Patent: December 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Nigel Walters, Nicholas Ngoly, David Cerantola, Mark Cunningham, Roger Lachance
  • Low hub-to-tip ratio fan for a turbofan gas turbine engine
    Patent number: 10408223
    Abstract: A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.
    Type: Grant
    Filed: June 7, 2017
    Date of Patent: September 10, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kari Heikurinen, Peter Townsend
  • Low hub-to-tip ratio fan for a turbofan gas turbine engine
    Patent number: 9709070
    Abstract: A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.
    Type: Grant
    Filed: February 24, 2016
    Date of Patent: July 18, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Karl Heikurinen, Peter Townsend
  • Filter cover protection against external contamination
    Patent number: 11638889
    Abstract: A fluid filter arrangement, with protection against external contamination, the filter arrangement comprising: a fluid circulating system; a filter cartridge having an exterior surface; a housing having an internal fluid chamber surrounding the exterior surface of the filter cartridge, an open end through which the filter cartridge can pass along a housing axis; and a cover sealed over the open end of the housing in a closed position, the cover in an open position exposing the open end of the housing, the cover including a fluid passage in communication with the internal fluid chamber in the closed position, the cover fluid passage being in communication with the fluid circulating system in the closed position and in the open position.
    Type: Grant
    Filed: September 25, 2019
    Date of Patent: May 2, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Paul Weaver, Rose Beaulieu, Pierre Gauvin, Louis Brillon
  • TURBINE ENGINE HEAT RECUPERATOR PLATE AND PLATE STACK
    Publication number: 20130199152
    Abstract: A heat recuperator includes a plurality of channel walls composed substantially of thermally-conductive material and supported in spaced-apart relation, defining fluid channels and interstices therebetween. The fluid channels receive at least one primary fluid flow and the interstices receive at least one secondary fluid flow so as to effect heat exchange between the two flows. In use, the plurality of channel walls are deformable by pressure differential between the primary and secondary fluid flows. When at least some of the channel walls are in a deformed state, the plurality of channel walls are stabilized through press fit engagement of mutually opposed contact regions formed in adjacent pairs of the channel walls.
    Type: Application
    Filed: February 3, 2012
    Publication date: August 8, 2013
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: David Harold MENHEERE, Andreas ELEFTHERIOU, Daniel T. ALECU, Quantai LIU
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