Search Patents
  • Internally cooled gas turbine airfoil and method
    Patent number: 7156620
    Abstract: An internally cooled airfoil for a gas turbine engine, wherein a plurality of elongated cooling fins are provided inside the concave sidewall.
    Type: Grant
    Filed: December 21, 2004
    Date of Patent: January 2, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Michael Leslie Clyde Papple
  • Coverplate deflectors for redirecting a fluid flow
    Patent number: 7189055
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: March 13, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remo Marini, Sri Sreekanth
  • Internally cooled gas turbine airfoil and method
    Patent number: 7156619
    Abstract: An internally cooled airfoil for a gas turbine engine, wherein a plurality of elongated cooling fins are provided inside the concave sidewall between two crossovers.
    Type: Grant
    Filed: December 21, 2004
    Date of Patent: January 2, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Michael Leslie Clyde Papple
  • Blade and disk radial pre-swirlers
    Patent number: 7189056
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: March 13, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Remo Marini
  • Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
    Patent number: 7244104
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: July 17, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Remo Marini
  • Shroud segment cooling configuration
    Patent number: 8246297
    Abstract: An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface.
    Type: Grant
    Filed: July 21, 2008
    Date of Patent: August 21, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kapila Jain, Marc Tardif
  • Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavities
    Patent number: 7520715
    Abstract: A shroud segment of a turbine shroud of a gas turbine engine comprises a platform with front and rear legs. The platform defines a plurality of axially extending holes with individual inlets on an outer surface of the platform for transpiration cooling of the platform of the turbine shroud segment.
    Type: Grant
    Filed: July 19, 2005
    Date of Patent: April 21, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Assaf Farah
  • Turbine shroud segment with integrated impingement plate
    Patent number: 8784037
    Abstract: A turbine shroud segment is metal injection molded (MIM) about an insert having a cooling air cavity covered by an impingement plate. The insert is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the insert.
    Type: Grant
    Filed: August 31, 2011
    Date of Patent: July 22, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Turbine shroud cooling system
    Patent number: 7063503
    Abstract: A cooled turbine shroud assembly includes a first cooling path and a second cooling path adapted to provide shroud impingement air at different pressures to enhance efficiency. The cooling air is preferably acquired from a common source of secondary air. In one aspect the assembly, a shroud support supports a shroud ring and the cooling paths are separated in part by a flexible seal.
    Type: Grant
    Filed: April 15, 2004
    Date of Patent: June 20, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: David Meisels
  • HEAT EXCHANGER TO COOL TURBINE AIR COOLING FLOW
    Publication number: 20100139288
    Abstract: A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, the portion of the compressor air flow being thereby cooled by the portion of the bypass air flow through the common wall
    Type: Application
    Filed: December 10, 2008
    Publication date: June 10, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Guiseppe RAGO
  • Interturbine vane with multiple air chambers
    Patent number: 8511969
    Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: August 20, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Nicolas Grivas
  • Interturbine vane with multiple air chambers
    Patent number: 8876463
    Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.
    Type: Grant
    Filed: July 16, 2013
    Date of Patent: November 4, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Nicolas Grivas
  • Sealing for vane segments
    Patent number: 8500392
    Abstract: A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: August 6, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon
  • Oil tube with integrated heat shield
    Patent number: 8596959
    Abstract: A gas turbine engine has an oil tube for delivering oil through a high temperature zone of the engine to an engine component for cooling and lubrication. An insulation tube surrounds the oil tube and extends in a substantial length of the oil tube. The opposed ends of the insulation tube are integrally and sealingly connected to respective end portions of the oil tube to form a dead air annulus between the oil tube and the insulation tube.
    Type: Grant
    Filed: October 9, 2009
    Date of Patent: December 3, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Watson
  • Active tip clearance control arrangement for gas turbine engine
    Patent number: 8092146
    Abstract: An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance.
    Type: Grant
    Filed: March 26, 2009
    Date of Patent: January 10, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Pierre-Yves Legare, Stephen Mah
  • Blade outer air seal cooling
    Patent number: 8740551
    Abstract: A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: June 3, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Franco Di Paola, Kapila Jain
  • Engine case with wash system
    Patent number: 8632299
    Abstract: A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct.
    Type: Grant
    Filed: November 30, 2010
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andreas Eleftheriou, David Menheere, Richard Ivakitch, Enzo Macchia
  • BYPASS AIR SCOOP FOR GAS TURBINE ENGINE
    Publication number: 20100150700
    Abstract: A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine.
    Type: Application
    Filed: December 16, 2008
    Publication date: June 17, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Steven STRECKER, Hong-Wei HUI
  • Heat exchanger to cool turbine air cooling flow
    Patent number: 8181443
    Abstract: A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, the portion of the compressor air flow being thereby cooled by the portion of the bypass air flow through the common wall.
    Type: Grant
    Filed: December 10, 2008
    Date of Patent: May 22, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Guiseppe Rago
  • Turbine housing assembly
    Patent number: 10815829
    Abstract: The turbine housing assembly includes a housing surrounding a plurality of turbine shroud segments mounted to support members of the housing. Impingement holes extend through the housing and have outlet openings communicating with a cavity between the shroud segments and the support. A deflector rail protrudes axially away from the support members into the cavity. The deflector rail defines a flow-redirecting surface to redirect the cooling air flow from the impingement holes radially outwardly, away from the turbine shroud segments.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kapila Jain, Patricia Phutthavong, Marc Tardif, Ho-Wing Leung