Search Patents
  • Reverse-flow gas turbine engine with electric motor
    Patent number: 11624319
    Abstract: A reverse-flow gas turbine engine includes a core of the gas turbine engine comprising multiple spools rotatable about a center axis of the gas turbine engine. Each spool is configured to pressurize air and to extract energy from combustion gases. The air and combustion gases are configured to flow through the core in a forward direction from an air inlet at an aft end of the core to an outlet at a forward end of the core. A propeller is disposed forward of the outlet. A reduction gearbox (RGB) is drivingly engaged to the core. An electric motor is drivingly engaged to the propeller and disposed axially between the RGB and the propeller.
    Type: Grant
    Filed: May 15, 2020
    Date of Patent: April 11, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Guy Lefebvre
  • Gas turbine engine with fuel-cooled turbine
    Patent number: 11459953
    Abstract: The gas turbine engine includes a combustion section including an annular swirl combustor having a combustor inlet, and a compressor section including a centrifugal compressor with an impeller, the impeller compressing and swirling an airflow and discharging the compressed and swirled airflow from the impeller outlet into the combustor inlet. The turbine section includes a radial turbine having a turbine fuel inlet and a turbine fuel outlet, the radial turbine receiving a flow of fuel at the turbine fuel inlet and discharging the flow of fuel from the turbine fuel outlet of the radial turbine into the combustor inlet.
    Type: Grant
    Filed: February 24, 2020
    Date of Patent: October 4, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Van Den Ende, David Menheere, Timothy Redford
  • Engine with start assist
    Patent number: 11028778
    Abstract: An engine includes a first power source configured to drive a first power input, a power output, and a transmission engaged with the first power input and the power output. The transmission includes an epicyclic gear train engaged with the first power input and selectively engageable with the power output. A brake is engageable in a drive condition with the epicyclic gear train to transfer power from the first power input to the power output. The brake in a start condition is disengageable to decouple the first power input from the power output. A start assist motor associated with a second power source is engaged with the transmission to rotate the power output.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: June 8, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Roberto Brito
  • Compressor rotor airfoil
    Patent number: 9765795
    Abstract: A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
    Type: Grant
    Filed: August 27, 2014
    Date of Patent: September 19, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Krishna Prasad Balike, Thomas Veitch, Raman Warikoo, Keegan Lobo
  • Wankel engine rotor
    Patent number: 9593580
    Abstract: A rotor for a Wankel engine including a plurality of ribs extending from a bearing support to each one of the flanks, the plurality of ribs including, for each flank, first and second ribs connected to the flank between the recess and a respective one of the apex portions. The first and second ribs are curved along at least a portion thereof, and/or the first and second ribs are closest to the respective apex portion and connected to the flank adjacent a junction between a portion of the flank defining the recess and a respective portion of the flank connected thereto. A method of reducing pinching of apex seals in a rotor of a Wankel engine is also discussed.
    Type: Grant
    Filed: November 23, 2012
    Date of Patent: March 14, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean-Gabriel Gauvreau, David Gagnon-Martin
  • Gas turbine combustor exit duct and hp vane interface
    Patent number: 8166767
    Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.
    Type: Grant
    Filed: October 15, 2010
    Date of Patent: May 1, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nicolas Grivas, Bhawan B. Patel, Oleg Morenko, Eric Durocher
  • Method of surge detection
    Patent number: 5402632
    Abstract: The double derivative of the gas generator shaft (16) is sensed and compared to upper and lower limits to determine breaches of these limits within a first predetermined time, in which case a first potential surge condition is declared. The derivative of torque, or the double derivative of shaft speed, of the power shaft (22) is sensed and compared to upper and lower limits to determine breaches of these limits within a second predetermined time, in which case a second potential surge condition is declared. If both a first and second potential surge condition is declared within a third predetermined time, an actual surge condition is declared.
    Type: Grant
    Filed: February 22, 1994
    Date of Patent: April 4, 1995
    Assignee: Pratt & Whitney Canada, Inc.
    Inventors: Anthony Nobre, Daniel Gratton
  • Gas turbine combustor exit duct and HP vane interface
    Patent number: 7836702
    Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.
    Type: Grant
    Filed: September 15, 2006
    Date of Patent: November 23, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nicolas Grivas, Bhawan B. Patel, Oleg Morenko, Eric Durocher
  • Turbine engine having improved high pressure turbine cooling
    Patent number: 6227801
    Abstract: A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and over a high work turbine blade at a lower static pressure than the diverted air to cool the blade. Advantageously, as the diverted air is relatively cool, use of a conventional TOBI nozzle may be eliminated. Similarly, showerheads on the blade may be eliminated. As well, the diverted air may conveniently be used to seal a rear bearing compartment within the engine.
    Type: Grant
    Filed: April 27, 1999
    Date of Patent: May 8, 2001
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Xiaoliu Liu
  • Brush seal assembly and method
    Patent number: 10844741
    Abstract: A brush seal assembly is adapted to be operatively mounted between a stator and a rotor of a gas turbine engine. The brush seal assembly comprises a housing and a seal operatively coupled to the housing. The seal comprises at least two annular brushes each having a plurality of bristles extending away from the housing. The at least two annular brushes and the housing defines a cavity therebetween. The housing defines at least one circumferential surface within the cavity. The housing comprises at least one discontinuity defined in the at least one circumferential surface. The at least one discontinuity disrupts a continuity of annularity of the circumferential surface.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: November 24, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Daniel Coutu, Nicola Houle
  • Seal assembly for a gas turbine engine
    Patent number: 5971703
    Abstract: An assembly for improving the operation of a gas turbine engine having an annular turbine support case and a plurality of shroud segments supported on the inner, radial side of the turbine support case. The shroud segments are located end-to-end to form an annular shroud within the turbine support case. Slots are provided in each of the adjacent ends of adjacent shroud segments, and seals are provided for insertion in the slots for sealing the gaps between the adjacent ends of adjacent shroud segments. The seals further include extensions which cooperate with the turbine support case to prevent rotation of the shroud segments relative to the turbine support case.
    Type: Grant
    Filed: December 5, 1997
    Date of Patent: October 26, 1999
    Assignee: Pratt & Whitney Canada Inc.
    Inventor: Guy Bouchard
  • Noise attenuating device for butterfly valves
    Patent number: 5881995
    Abstract: A noise attenuating device for reducing the noise generated by a gas flow passing through an open butterfly valve having a disc pivotally mounted in a valve housing for rotation about a transversal axis between an open and a closed position thereof. The noise attenuating device comprises a first series of elongated members extending from the upstream side of the disc above the transversal axis and a second series of generally diametrically opposed elongated members extending from the downstream side of the disc below the horizontal axis. Typically, the elongated members extend at 45 degree from the disc of the butterfly valve.
    Type: Grant
    Filed: December 15, 1997
    Date of Patent: March 16, 1999
    Assignee: Pratt & Whitney Canada Inc.
    Inventors: Man-Chun Tse, Hilaire Bonneau
  • Sensor probe with anti-icing
    Patent number: 9970824
    Abstract: Sensor probes with anti-icing and methods for manufacturing such sensor probes are disclosed. An exemplary sensor probe comprises a probe sensor, a probe body housing the probe sensor and an anti-icing device. The anti-icing device is bonded to and covers at least part of the probe body for preventing ice from forming on the probe body. The anti-icing device comprises a heating element thermally insulated from the probe body by a thermal insulator and a hydrophobic coating covering the heating element and defining an outer surface for exposure to an airflow. The heating element may be deposited using a direct write process.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: May 15, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kin-Leung Cheung, Peter Lance
  • Chuck for machine tool and sealing system
    Patent number: 11548076
    Abstract: A chuck for a machine tool includes a body rotatable about a rotation axis and defining a plurality of slots extending radially in the body, a plurality of jaws received in corresponding ones of the plurality of slots, the jaws being radially movable relative to the body between an inward position and an outward position, and for at least one of the plurality of jaws, a sealing layer disposed in the slot receiving the at least one of the plurality of jaws and sealing an interface between opposed lateral sides of the at least one jaw and a surface of the body defining the slot receiving the at least one of the plurality of jaws. A method of sealing an interface between a surface defining a slot of a chuck is also described.
    Type: Grant
    Filed: August 20, 2019
    Date of Patent: January 10, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lanoue, Philippe Raymond
  • Emergency power unit for electric aircraft
    Patent number: 11794914
    Abstract: Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.
    Type: Grant
    Filed: July 19, 2021
    Date of Patent: October 24, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ivan Sidorovich Paradiso, Daniel Alecu
  • High pressure turbine vane cooling hole distrubution
    Patent number: 8568085
    Abstract: A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
    Type: Grant
    Filed: July 19, 2010
    Date of Patent: October 29, 2013
    Assignee: Pratt & Whitney Canada Corp
    Inventors: Franco Di Paola, Larry Lebel, François Doyon
  • Normally open reverse flow flapper valve
    Patent number: 6851255
    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: Grant
    Filed: December 18, 2002
    Date of Patent: February 8, 2005
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Paul Archibald Aitchison, Patrick David Germain, Henry Smith
  • Electric machine systems
    Patent number: 11011966
    Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.
    Type: Grant
    Filed: December 7, 2018
    Date of Patent: May 18, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Latulipe, Richard Freer
  • NOZZLE TIP WITH SHIELDED CORE FOR A DUAL COMBUSTION SYSTEMS
    Publication number: 20220364509
    Abstract: In one aspect of the present disclosure, there is provided a nozzle assembly comprises a first fuel conduit defined between a nozzle body and a fuel swirler and extending along a longitudinal axis from an inlet of the first fuel conduit to an outlet of the fuel nozzle assembly. A second fuel conduit is defined between the fuel swirler and a heat shield and extending along the fuel swirler along the longitudinal axis from an inlet of the second fuel conduit to the outlet of the fuel nozzle assembly. An air conduit extends through the heat shield along the longitudinal axis from an inlet of the air conduit to the outlet of the fuel nozzle assembly.
    Type: Application
    Filed: May 17, 2021
    Publication date: November 17, 2022
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Oleg Morenko, Sandeep Vishal Dhalla
  • Deformable bumper for a rotating structure of a turbine engine
    Patent number: 11384658
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a stationary structure, a rotating structure, a bearing. The rotating structure rotatable about an axis relative to the stationary structure. The bearing supports the rotating structure. The stationary structure includes a flexible bearing support and a crushable bumper. The flexible bearing support supports the bearing. The crushable bumper is arranged radially outward of and axially overlaps the flexible bearing support. The stationary structure is configured such that: the flexible bearing support is disengaged from the crushable bumper during a first mode of operation; and the flexible bearing support contacts the crushable bumper during a second mode of operation.
    Type: Grant
    Filed: August 19, 2021
    Date of Patent: July 12, 2022
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Stephen Caulfeild
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