Search Patents
  • 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
  • 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: 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
  • Blade under platform pocket cooling
    Patent number: 8152436
    Abstract: Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.
    Type: Grant
    Filed: January 8, 2008
    Date of Patent: April 10, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David F. Glasspoole, François Caron
  • Airfoil platform impingement cooling
    Patent number: 7452184
    Abstract: A gas turbine engine airfoil has a platform cooling scheme including an impingement hole for directing cooling air against an undersurface of the airfoil platform.
    Type: Grant
    Filed: December 13, 2004
    Date of Patent: November 18, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Remy Synnott, Dany Blais
  • 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
  • Shroud leading edge cooling
    Patent number: 7246989
    Abstract: A cooling device includes a plurality of passages extending through outer platforms of turbine vane segments for directing cooling air in a choked flow condition towards a downstream turbine shroud.
    Type: Grant
    Filed: December 10, 2004
    Date of Patent: July 24, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David Glasspoole, Ricardo Trindade
  • Rotor assembly with cooling air deflectors and method
    Patent number: 7354241
    Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises a plurality of cooling air deflectors made integral with the rotor disk to redirect air to a manifold at a bottom side of a corresponding blade retention slot on the periphery of the rotor disk.
    Type: Grant
    Filed: November 2, 2006
    Date of Patent: April 8, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Toufik Djeridane, Michael Leslie Clyde Papple, Sri Sreekanth, Alan Juneau, Dominique Michel Nadeau
  • Internally cooled airfoil
    Patent number: 9810071
    Abstract: An internally cooled airfoil for a gas turbine engine has a hollow airfoil body defining a core cavity. An insert is mounted in the core cavity. A cooling gap is provided between the insert and the hollow airfoil body. A plurality of standoffs project across the cooling gap. Trip-strips projecting laterally between adjacent standoffs. The trip-strips and the standoffs may be integrated into a unitary heat transfer feature.
    Type: Grant
    Filed: September 27, 2013
    Date of Patent: November 7, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michael Papple
  • Turbine disc and retaining nut arrangement
    Patent number: 8186939
    Abstract: A turbine rotor for a gas turbine engine including a disc having a hub defining a central bore for receiving an engine shaft. A nut retains the disc on the shaft. The disc retaining nut has at least one cooling passage defined therein and disposed for directing a flow of cooling air passing through the bore of the disc.
    Type: Grant
    Filed: August 25, 2009
    Date of Patent: May 29, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Daniel Lecuyer, Alain Carrieres, Franco Di Paola
  • Method for fan blade heating using coanda effect
    Patent number: 11118457
    Abstract: A method of heating a fan blade of a gas turbine engine for anti-icing includes emitting jets of heated air from a radial fin disposed upstream from a radially inward portion of a fan blade airfoil, the jets of heated air being directed by outlet orifices in a downstream direction substantially parallel to a flow of incoming air over the fan blade airfoil.
    Type: Grant
    Filed: October 21, 2019
    Date of Patent: September 14, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Ivakitch, David Menheere, Paul Stone
  • 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
  • ENGINE CASE WITH WASH SYSTEM
    Publication number: 20120134777
    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: Application
    Filed: November 30, 2010
    Publication date: May 31, 2012
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas ELEFTHERIOU, David MENHEERE, Richard IVAKITCH, Enzo MACCHIA
  • Gas turbine engine feather seal arrangement
    Patent number: 5531457
    Abstract: Adjacent platforms (16) have feather seals (34) in complementary slots (22). Hot grooves (40) carry cooling air across the seal and discharge it into the gap (20) between adjacent platforms. Grooves discharging from abutting surfaces are staggered and have a flow component parallel to the axial gas flow through the turbine.
    Type: Grant
    Filed: December 7, 1994
    Date of Patent: July 2, 1996
    Assignee: Pratt & Whitney Canada, Inc.
    Inventors: Ian Tibbott, Roger Gates
  • Rotor disk for gas turbine engine
    Patent number: 10927676
    Abstract: A gas turbine engine rotor disk has a single-piece hub with a radially-outer surface, and with an annular cavity inside the single-piece hub. The annular cavity is defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation. Blades extend outwardly from the radially-outer surface.
    Type: Grant
    Filed: February 5, 2019
    Date of Patent: February 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Ho, Jamal Zeinalov
  • Cooled airfoil component
    Patent number: 8007237
    Abstract: A gas turbine engine airfoil component having an airfoil body with a core cavity, an end opening in communication with the core cavity, and a wall having a plurality of cooling holes defined therein, each cooling hole being oriented such that the respective hole axis extends out of the core cavity through the end opening.
    Type: Grant
    Filed: December 29, 2006
    Date of Patent: August 30, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sri Sreekanth, Michael Papple
  • Rotor assembly with cooling air deflectors and method
    Patent number: 7192245
    Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises a plurality of cooling air deflectors mounted on the rotor assembly to redirect air to a manifold at a bottom side of a corresponding blade retention slot on the periphery of the rotor disk.
    Type: Grant
    Filed: December 3, 2004
    Date of Patent: March 20, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Toufik Djeridane, Michael Leslie Clyde Papple, Sri Sreekanth, Alan Juneau, Dominique Michel Nadeau
  • INTERTURBINE VANE WITH MULTIPLE AIR CHAMBERS
    Publication number: 20110081228
    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: Application
    Filed: October 1, 2009
    Publication date: April 7, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric DUROCHER, Nicolas GRIVAS
  • Cooled turbine vane platform
    Patent number: 7004720
    Abstract: A vane assembly for a gas turbine engine comprises a plurality of airfoils extending between platforms and a plurality of effusion holes which are defined in at least one of the inner and outer platforms in a region intermediate adjacent airfoils. The effusion holes provide fluid flow communication between a cooling air source and the gas path.
    Type: Grant
    Filed: December 17, 2003
    Date of Patent: February 28, 2006
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remy Synnott, Ricardo Trindade
  • Vane assembly with removable vanes
    Patent number: 8182213
    Abstract: A vane assembly for a gas turbine engine where each vane is connected to at least one adjacent portion of at least one of the inner and the outer shrouds through a melt-weld connection. The melt-weld connection includes non-metallic heat-meltable material with a metal wire mesh layer trapped therein, the metal wire mesh being heatable to melt the heat-meltable material for formation and breakdown of the melt-weld connection.
    Type: Grant
    Filed: April 22, 2009
    Date of Patent: May 22, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Kin-Leung Cheung