Search Patents
  • Gas turbine engine and method of operation
    Patent number: 11867126
    Abstract: The gas turbine engine can have an engine core; a core output shaft drivable by the engine core; a power output shaft; an auxiliary power shaft; and a reduction gearbox having gears, the gears drivingly connecting the core output shaft to the auxiliary power shaft. The gears can include an epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft. The gas turbine engine can further have a second auxiliary power shaft interconnected to the auxiliary power shaft, the power output shaft, and the core output shaft by the gears.
    Type: Grant
    Filed: July 13, 2021
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruno Chatelois, Michel Desjardins, Paul Weaver, Eric Durocher
  • Diffuser pipe alignment tool
    Patent number: 11988229
    Abstract: A method of positioning exits of diffuser pipes of a centrifugal compressor in an aircraft engine includes aligning an alignment tool with a structure supporting the diffuser pipes, and rotating each diffuser pipe about an inlet axis thereof to close a gap between a surface of the diffuser pipe and part of the alignment tool until the diffuser pipe abuts the part of the alignment tool. The alignment tool includes for example a body defining a center axis and having at least one tool datum configured for abutting against the casing, and a plurality of alignment members that are fixed to the body and extend radially from the body relative to the center axis.
    Type: Grant
    Filed: June 8, 2023
    Date of Patent: May 21, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gavin Rohiteshwar Kisun, Danny Noiseux
  • Gas turbine engine yoke and build support
    Patent number: 11248497
    Abstract: A gas turbine engine yoke includes an arcuate body mountable to a stand and rotatable between an upright orientation and a horizontal orientation. The body has an inner wall spaced apart from an outer wall and first and second side walls extending between the inner and outer walls. A mounting plane of the yoke extends through the inner and outer walls and is positioned between the first and second side walls. Engine attachments are spaced apart along the inner wall and lie in the mounting plane. A method of assembling the gas turbine engine is also disclosed.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: February 15, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Carlo Porco, Geoffrey Henriksen, Jason Wedemire, Anthony Mathias, David Nicol, Filip Ristovski
  • 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
  • Compressor rotor airfoil
    Patent number: 10760424
    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 11, 2017
    Date of Patent: September 1, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Krishna Prasad Balike, Thomas Veitch, Keegan Lobo, Raman Warikoo
  • Protective saddle mount for cable tie
    Patent number: 7861981
    Abstract: A method and apparatus for providing a mounting system for an elongated item such as a cable, tube or wire, or an assembly of multiple cables, tube and/or wires. The mounting system includes an apparatus for mounting to a supporting structure, and an apparatus for receiving the elongated item. Also included is an apparatus for receiving a tying member such as a cable tie. Also included is an apparatus for permitting the tying member to be cut to release the elongate item from the mount without damage to the elongate item.
    Type: Grant
    Filed: October 22, 2008
    Date of Patent: January 4, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Bryan William Olver
  • METHODS AND SYSTEMS FOR CALCULATION OF FEEDRATE
    Publication number: 20140148942
    Abstract: Methods and systems for calculating a feedrate for programming a multi-axis machining tool. For at least one control block in a defined machining path: a displacement of a defined machine control point from a previous control block to a current control block is determined; a displacement of a defined feedrate control point from the previous control block to the current control block is determined; a compensation ratio is calculated as a ratio between the displacement of the defined machine control point and the displacement of the defined feedrate control point; and a feedrate for the machine control point is calculated by applying the compensation ratio to a desired feedrate. The calculated federate is used in a control block of a multi-axis machining tool.
    Type: Application
    Filed: November 27, 2012
    Publication date: May 29, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Vincent THOMASSET-LAPERRIERE, Amr ELFIZY
  • 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
  • Combustor wall assembly for gas turbine engine
    Patent number: 11536454
    Abstract: Wall assemblies for a combustor of a gas turbine engine are disclosed. A wall assembly comprises an outer shell made of a metallic material, adjacent first and second inner panels mounted to the outer shell via an insert and a damper disposed between the outer shell and at least one of the first and second inner panels. The first and second inner panels may be spaced apart from the outer shell to define a double-wall configuration with the outer shell. The first and second inner panels may be made of a composite material. The insert may be made from substantially the same or other type of composite material.
    Type: Grant
    Filed: December 16, 2019
    Date of Patent: December 27, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Tin-Cheung John Hu
  • System and method for detecting propeller malfunction
    Patent number: 11866151
    Abstract: A system and method for detecting fixed pitch operation of a variable pitch propeller of an engine are provided. A command signal for maintaining a rotational speed of the propeller at a reference speed is output. An actual value of at least one of the rotational speed and a blade angle of the propeller is obtained. From the actual value, it is assessed whether an expected change in the at least one of the rotational speed and the blade angle of the propeller has occurred in response to the command signal. Responsive to determining that the expected change in the at least one of the rotational speed and the blade angle of the propeller has not occurred in response to the command signal, operation of the propeller at fixed pitch is detected and an alert output accordingly.
    Type: Grant
    Filed: December 23, 2020
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Jagoda Krzywon
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • Method of manufacturing a heat shield for a fuel manifold
    Patent number: 7559142
    Abstract: A method of manufacturing a heat shield for a manifold ring of a gas turbine engine, comprising forming a tubular portion of heat shield material with an arcuate longitudinal axis, deforming the tubular portion such that a cross-section thereof defines a profile corresponding to at least two complementary heat shield portions configured to cooperate to significantly surround at least a circumferential portion of the manifold ring, and cutting the tubular portion to divide the tubular portion into each of the heat shield portions.
    Type: Grant
    Filed: October 24, 2006
    Date of Patent: July 14, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
  • 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 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
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