Search Patents
  • Non-contacting seal with non-abradable coating
    Patent number: 10954820
    Abstract: There is provided a non-contacting seal assembly for a gas turbine engine, having a housing that houses a sealing ring; and a counter component cooperating with the sealing ring. The sealing ring and the counter component are rotatable relative to each other about a central axis and define sealing faces circumferentially extending around the central axis. The sealing faces face each other and are spaced apart from each other by a controlled gap. At least one of the sealing faces is coated with a non-abradable material. A method of operating a non-contacting seal assembly is also provided.
    Type: Grant
    Filed: January 31, 2018
    Date of Patent: March 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Alexander Smith
  • COUPLING ELEMENT FOR TORQUE TRANSMISSION IN A GAS TURBINE ENGINE
    Publication number: 20140116061
    Abstract: A gas turbine engine having a coupling element for coupling a first shaft to a second shaft, the second shaft being substantially axially aligned with the first shaft, the coupling element provided with an exterior surface that engages an opposing interior surface of the first shaft and an interior surface that engages an opposing exterior surface of the second shaft to facilitate torque transfer between the first shaft and the second shaft when rotated together, wherein the coupling element and at least one of the first and second shafts cooperate to define at least one fluid passageway therebetween.
    Type: Application
    Filed: October 25, 2012
    Publication date: May 1, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Barry BARNETT, Phillipe BONNIERE, Daniel ALECU
  • Gear with optimized gear web shape
    Patent number: 10072732
    Abstract: A gear comprises gear teeth. An annular web has the gear teeth on an external surface thereof and rotatable about a rotational axis of the gear. The web comprises a wall having at least a first axial surface and a second axial surface on the opposite side of the wall. The web defined by a first web section in which the first axial surface, in an inward direction, inclines away from a radial plane to which the rotational axis is normal, a second web section radially inward of the first web section, and in which the first axial surface, in the inward direction, inclines toward said radial plane.
    Type: Grant
    Filed: November 19, 2014
    Date of Patent: September 11, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Alain Carrieres
  • System and method for synthesizing engine thrust
    Patent number: 11674450
    Abstract: A method and a system for synthesizing thrust from a turbofan engine are provided. The turbofan engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine, a pressure of fluid at an exit of the compressor section and a temperature of fluid at a location upstream of the exit of the compressor section are determined. A synthesized value of thrust from the turbofan engine is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine is output.
    Type: Grant
    Filed: December 13, 2021
    Date of Patent: June 13, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Labrecque, Kevin Nguyen, Ninad Joshi
  • Boss for gas turbine engine
    Patent number: 11384659
    Abstract: A gas turbine engine, has: a case extending circumferentially around a central axis of the gas turbine engine; a boss protruding from the case away from the central axis, the boss defining an internal passage; a tubular member received within the internal passage of the boss and secured to the boss; an annular gap extending all around the tubular member and located between the tubular member and the boss; and a fitting hydraulically connecting a fluid source to the tubular member, the fitting having a portion received within the tubular member and encircled by both of the annular gap and the tubular member, the fitting sealingly engaged to the tubular member.
    Type: Grant
    Filed: September 11, 2020
    Date of Patent: July 12, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Method of shaping green part and manufacturing method using same
    Patent number: 9517507
    Abstract: A method of shaping a part in a green state obtained through powder injection molding, including placing a surface of the part in contact with a shaping surface of a setter with at least one section of the surface of the part not conforming to the shaping surface, and locally heating at least one area of each of the at least one section to deform the part until the at least one section conforms to the shaping surface. The part remains in the green state during the local heating. The part may be a heat shield panel for a gas turbine engine.
    Type: Grant
    Filed: July 17, 2014
    Date of Patent: December 13, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marc Campomanes, Orlando Scalzo, Guillaume Poitras
  • Fuel air heat exchanger
    Patent number: 8943827
    Abstract: A gas turbine engine with a fuel air heat exchanger located in the high pressure plenum. The heat exchanger includes at least one air conduit and at least one fuel conduit in heat exchange relationship with one another, with a fuel flow communication between a fuel source and fuel distribution members of the combustor being provided at least partly through the at least one fuel conduit, and the at least one air conduit defining a fluid flow communication between the high pressure plenum and an engine component to be cooled by the compressed air.
    Type: Grant
    Filed: May 31, 2011
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Eduardo Hawie
  • Method of protecting a surface
    Patent number: 9126232
    Abstract: A method of masking part of a surface of a wall of a gas turbine component including at least one area having cooling holes defined therein, the method including applying a viscous curable masking compound to the part of the surface over an entirety of each of the at least one area, including blocking access to the cooling holes from the surface by applying the masking compound over the cooling holes without completely filling the cooling holes with the masking compound, and forming a respective solid masking element completely covering each of the at least one area and the cooling holes defined therein by curing the masking compound.
    Type: Grant
    Filed: February 21, 2013
    Date of Patent: September 8, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Philippe Saint-Jacques
  • Standing wave excitation cavity fluid pump
    Patent number: 6672847
    Abstract: A pump includes an outer body; and a wall within said outer body. The outer body and the wall define a pumping cavity and an excitation cavity within the outer body. An excitable medium is contained within the excitation cavity. An excitation source is coupled to said excitable medium. This excitation source is operable to excite the excitable medium and create a standing wave therein. The standing wave acts through the wall to pump said fluid through said pumping cavity. Advantageously, the excitable medium is isolated from the pumped fluid by the wall.
    Type: Grant
    Filed: December 27, 2001
    Date of Patent: January 6, 2004
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Kevin Allan Dooley
  • Anti-icing apparatus and method for aero-engine nose cone
    Patent number: 7581378
    Abstract: An aero-engine nose cone anti-icing system (10) using a rotating heat pipe (12) is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source (36) within the engine (22) to the nose cone (18) through a rotating heat pipe (12) along the central shaft (16). A condenser (20) and evaporator (14) are provided which are adapted to the heat transfer requirements and space constraints in the engine (22).
    Type: Grant
    Filed: July 28, 2006
    Date of Patent: September 1, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Joseph Horace Brand, Michael John Dowhan
  • Internal fuel manifold and fuel fairing interface
    Patent number: 7703286
    Abstract: A mounting system for an annular internal fuel manifold disposed within a gas turbine engine includes a fuel inlet assembly having a heat shield extending about at least a portion of an inner fuel inlet tube. The heat shield has a distal end engaged with the fuel manifold and has a radially outwardly projecting shoulder proximate an opposed proximal end thereof. The proximal end of the heat shield is received within a bushing disposed within a corresponding opening of a supporting casing. The shoulder of the heat shield retains the bushing in place.
    Type: Grant
    Filed: September 22, 2006
    Date of Patent: April 27, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Oleg Morenko, Bryan Olver
  • Pneumatic compressor bleed valve
    Patent number: 6755025
    Abstract: A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve plug on the piston and an annular valve seat on the compressor housing defining a valve seal interface. A control air pressure conduit communicates between a portion of the annular chamber bounded by the piston and a source of control air pressure. Guide bearings mounted to the periphery of the piston and the housing have a helical guide surface concentric the engine axis.
    Type: Grant
    Filed: July 23, 2002
    Date of Patent: June 29, 2004
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andreas Eleftheriou, Vittorio Bruno, Ian William Chandler
  • Method and apparatus for manufacturing compliant brush seals
    Patent number: 4884850
    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 clamping 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 30, 1988
    Date of Patent: December 5, 1989
    Assignee: Pratt & Whitney Canada, Inc.
    Inventor: John Greer
  • MID TURBINE FRAME FOR GAS TURBINE ENGINE
    Publication number: 20100132376
    Abstract: A mid turbine frame of a gas turbine engine includes an outer case which supports a spoke casing co-axially positioned therein. The spoke casing has load transfer spokes extending radially from an inner case and secured to the outer case. A load transfer device is provided to transfer load from the spokes to the outer case in addition to load transfer through a first group of fasteners securing the spokes to the outer case, thereby forming a secondary load transfer path from the spokes. The load transfer device includes an opening of the outer case into which at least some of the spokes are inserted.
    Type: Application
    Filed: November 28, 2008
    Publication date: June 3, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON
  • System and method for variable geometry mechanism control
    Patent number: 10605166
    Abstract: A system and method for controlling a variable inlet geometry mechanism of an aircraft engine. At least one first input signal indicative of at least one operating parameter of an aircraft engine is received. At least one second input signal indicative of a level of crosswind experienced by the aircraft and of an airspeed of the aircraft being below a predetermined threshold is received. A schedule is determined for positioning a the variable inlet geometry mechanism based on the at least one first input signal and of the at least one second input signal. The variable inlet geometry mechanism is then positioned in accordance with the schedule.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: March 31, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andrew Roach, Wai-Lyn Wong, Sebastian Jaehun Kim
  • Gas turbine engine tip clearance control system
    Patent number: 11085319
    Abstract: A system for controlling gas turbine engine rotor blades tip clearance is described. A rotor is mounted to an engine shaft, supported by a thrust bearing, for rotation within a gas path shroud circumscribing blades of the rotor, the gas path shroud having a non-cylindrical shape in the vicinity of the rotor blades. A rotary actuator is associated with the thrust bearing and configured for axial translation of the thrust bearing, to thereby axially translate the engine shaft and the rotor blades relative to the gas path shroud. This translation is configured to vary the blade tip clearance of the rotor.
    Type: Grant
    Filed: June 21, 2019
    Date of Patent: August 10, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Timothy Redford, David Menheere, Richard Kostka
  • Floatwall dilution hole cooling
    Patent number: 7726131
    Abstract: A combustor for a gas turbine engine is provided, the combustor having an outer shell with an outer surface exposed to cooling air and an inner surface, and at least one floatwall panel attached to the inner surface of the outer shell and having a trailing edge. At least one dilution hole is in the floatwall panel near the trailing edge and in communication with the outer surface of the outer shell, and at least one local air impingement hole is in the outer shell downstream of each at least one dilution hole, that directs the cooling air towards the trailing edge of the floatwall panel.
    Type: Grant
    Filed: December 19, 2006
    Date of Patent: June 1, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Robert Sze, Jeffrey Richard Verhiel
  • Power turbine blade airfoil profile
    Patent number: 10329915
    Abstract: A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: June 25, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Krishan Mohan, Panagiota Tsifourdaris, Lorenzo Sanzari, Igal Acher Abenhaim, Anthony Pham
  • Vane segment with ribs
    Patent number: 10876416
    Abstract: There is disclosed a vane segment for a gas turbine engine. The vane segment includes vanes extending radially from inner ends to outer ends. The vanes have leading edges, trailing edges, and chords extending from the leading edges to the trailing edges. A platform circumferentially extends around the central axis. The platform has an inner face facing the central axis and an opposed outer face. The inner face of the platform is connected to the outer ends of the vanes. Ribs protrude away from the outer face and have lengths extending along the outer face.
    Type: Grant
    Filed: July 27, 2018
    Date of Patent: December 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jonathan Tebeka, Franco Di Paola, Jasrobin Grewal
  • Shaft assembly for aircraft engine
    Patent number: 10968834
    Abstract: There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.
    Type: Grant
    Filed: June 28, 2019
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Labbe, Lukasz Pokrzywa
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