Search Patents
  • Airfoil cooling passage trailing edge flow restriction
    Patent number: 7278826
    Abstract: An internal metering structure permits the exit apertures of a cooled airfoil to be sized to provide for easy manufacturability.
    Type: Grant
    Filed: August 18, 2004
    Date of Patent: October 9, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Timothy Blaskovich, Larry Lebel, Ricardo Trindade
  • MULTI-MATERIAL TURBINE ENGINE SHAFT
    Publication number: 20100229387
    Abstract: A turbine engine shaft comprising an end section thereof made of high temperature resistant super-alloy adapted for working in a hot section of the engine, and a remaining section of the shaft made of steel. The end section and the remaining section are directly joined together to form a single-piece shaft.
    Type: Application
    Filed: January 26, 2009
    Publication date: September 16, 2010
    Applicant: Pratt & Whitney Canada Corp
    Inventor: Ioan Sasu
  • Annular gas turbine engine case and method of manufacturing
    Patent number: 8397383
    Abstract: The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform.
    Type: Grant
    Filed: October 2, 2006
    Date of Patent: March 19, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Barry Barnett, Steven Hunt, Czeslaw Wojtyczka
  • Gas turbine fuel nozzle manufacturing
    Patent number: 7497012
    Abstract: A method and a pre-shaped workpiece for making at least a portion of a gas turbine fuel nozzle are disclosed having opposed gripping tabs which can be secured to machine tool holders during manufacturing by a machine tool.
    Type: Grant
    Filed: December 21, 2004
    Date of Patent: March 3, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Harris Shafique, Lafleche Gagnon
  • METHOD FOR CENTERING ENGINE STRUCTURES
    Publication number: 20110078902
    Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components.
    Type: Application
    Filed: October 1, 2009
    Publication date: April 7, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON, Nicolas GRIVAS
  • Method of making a gas turbine engine diffuser
    Patent number: 7114255
    Abstract: A method of machining a plurality of intersecting bores in an object, the method comprising steps of machining a first bore, plugging the first bore, machining a second bore so as to intersect the first bore, and unplugging the first bore.
    Type: Grant
    Filed: November 26, 2003
    Date of Patent: October 3, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ioan Sasu, Bertrand Gendreau, Robert Francois Lanoue
  • Method and apparatus for providing rotor discs
    Patent number: 8925201
    Abstract: A method for providing a disc of a bladed rotor for use in a gas turbine engine including the steps of determining the location of blade fixing slots to be formed on the disc to receive the roots of respective blades, determining a virtual profile of each slot on the disc, and forming, prior to the slots being formed in the disc, a narrow, axial pilot slot centrally of the virtual profile of each slot.
    Type: Grant
    Filed: June 29, 2009
    Date of Patent: January 6, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Michel Frédérick
  • Helical channel for distributor and method
    Patent number: 7454914
    Abstract: A method of distributing fuel in a fuel nozzle comprises: providing at least two helical channels in the fuel nozzle, each having a channel exit port, providing a fuel inlet cavity in fluid communication with the helical channels, and flowing fuel in the fuel inlet cavity, the helical channels and the channel exit ports.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: November 25, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Lev Alexander Prociw
  • Method for centering engine structures
    Patent number: 8578584
    Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centering may be provided by machining selected contacting surfaces of selected components.
    Type: Grant
    Filed: October 19, 2012
    Date of Patent: November 12, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon, Nicolas Grivas
  • Method of fabricating integrally bladed rotor and stator vane assembly
    Patent number: 8631577
    Abstract: A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Visal Ing
  • Method of machining airfoil root fillets
    Patent number: 8100655
    Abstract: An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip portion defining a compound curve.
    Type: Grant
    Filed: March 28, 2008
    Date of Patent: January 24, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Paul Stone, Dinesh Chawla, Frank Kelly, Edward Fazari, Kari Heikurinen, Ignatius Theratil
  • Welded gas turbine engine parts with different thicknesses and method
    Patent number: 8443515
    Abstract: A welded part comprises a first detail and a second detail at least partially overlapping the first detail in an overlapping zone. A pair of side-by-side weld seams is provided in the overlapping zone to form a part suited for used in a gas turbine engine with the first and second details.
    Type: Grant
    Filed: August 31, 2006
    Date of Patent: May 21, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Oleg Morenko, Lorin Markarian, Bhawan B. Patel
  • FABRICATED ITD-STRUT AND VANE RING FOR GAS TURBINE ENGINE
    Publication number: 20100132377
    Abstract: A gas turbine engine mid turbine frame having an annular interturbine duct and vane ring assembly includes a duct having outer and inner duct walls of sheet metal interconnected by radial hollow struts of sheet metal and a vane ring is connected to the duct to provide the assembly. The interturbine duct and vane ring assembly may be provided within a mid turbine frame in a manner which is independent of a bearing load path through the mid turbine frame.
    Type: Application
    Filed: November 28, 2008
    Publication date: June 3, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, John PIETROBON
  • Method for centering engine structures
    Patent number: 8316523
    Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: November 27, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon, Nicolas Grivas
  • GAS TURBINE ENGINE THERMAL EXPANSION JOINT
    Publication number: 20110081234
    Abstract: A thermal expansion joint apparatus includes an insert extending passages passing through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine.
    Type: Application
    Filed: October 1, 2009
    Publication date: April 7, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, Guy LEFEBVRE
  • Method of assembly and disassembly of a gas turbine mid turbine frame
    Patent number: 8347500
    Abstract: A mid turbine frame with an annular interturbine duct may be assembled by placing an mid turbine frame inner case of into the interturbine duct, inserting a plurality of mid turbine frame spokes radially through respective hollow radial struts of the interturbine duct to be connected to the mid turbine frame inner case to form a mid turbine frame spoke casing. A mid turbine frame outer case is also connected to the spokes, to provide an assembled mid turbine frame.
    Type: Grant
    Filed: November 28, 2008
    Date of Patent: January 8, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon
  • Internal fuel manifold with turned channel having a variable cross-sectional area
    Patent number: 7607226
    Abstract: A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring such that the channel has a cross-sectional area that varies around a circumference of the ring.
    Type: Grant
    Filed: March 3, 2006
    Date of Patent: October 27, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Jason Fish, Dany Gaudet, Lafleche Gagnon
  • Method of manufacturing a metal injection moulded combustor swirler
    Patent number: 7721436
    Abstract: A combustor swirler for a gas turbine engine and method of manufacturing by metal injection molding an inner component and an outer cylindrical component. Indentations are molded in one of the inner and outer components and sealed by the engagement of the components together to form a series of fluid flow passages. The inner and outer components are molded with interlocking features for ensuring proper alignment of the components during assembly.
    Type: Grant
    Filed: December 20, 2005
    Date of Patent: May 25, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Harris Shafique, Aleksander Kojovic
  • Gas turbine engine thermal expansion joint
    Patent number: 8636465
    Abstract: A thermal expansion joint apparatus includes an insert extending through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert, thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: January 28, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Laser drilling methods of shallow-angled holes
    Patent number: 8624151
    Abstract: A method for drilling a shallow-angled hole through a thermal barrier coated component, in accordance with one aspect thereof, includes a step of applying a pulse laser beam with a first setting to drill a section of the hole substantially within a thermal barrier coating of the component. A further step is conducted to apply the pulse laser beam with a second setting through the initiated hole to further drill through a remainder of the component to complete the formation of the hole extending through the component.
    Type: Grant
    Filed: July 19, 2011
    Date of Patent: January 7, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Amr Elfizy, Ghislain Hardy, Sylvain Cournoyer