Patents by Inventor Remy Synnott

Remy Synnott has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20060127212
    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: Application
    Filed: December 13, 2004
    Publication date: June 15, 2006
    Inventors: Eric Durocher, Remy Synnott, Dany Blais
  • Publication number: 20060082074
    Abstract: A seal arrangement between a vane assembly and a static shroud assembly reduces gas path leakage and beneficially improves gas turbine performance.
    Type: Application
    Filed: October 18, 2004
    Publication date: April 20, 2006
    Inventors: Remy Synnott, David Glasspoole
  • Publication number: 20060083607
    Abstract: A ring seal for sealing an annular gap defined between opposed surfaces of concentric inner and outer annular engine parts in a gas turbine engine. The ring seal being wholly disposed within the annular gap and having a wave pattern with alternating peaks. The ring seal radially inwardly loads the inner engine part and provides a fluid seal between the inner and outer engine parts.
    Type: Application
    Filed: October 15, 2004
    Publication date: April 20, 2006
    Inventors: Remy Synnott, Dany Blais
  • Publication number: 20060045746
    Abstract: A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and second gas turbine engine components for spring loading the first and second gas turbine engine components relative to one another.
    Type: Application
    Filed: August 24, 2004
    Publication date: March 2, 2006
    Inventor: Remy Synnott
  • Publication number: 20060045745
    Abstract: A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing.
    Type: Application
    Filed: August 24, 2004
    Publication date: March 2, 2006
    Inventors: Remy Synnott, Nicolas Grivas, Alan Juneau, David Glasspoole
  • 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
  • Publication number: 20050287001
    Abstract: Random air flow leakage between a shroud assembly and a stator vane assembly into the gas path of a gas turbine engine due to manufacturing tolerance stack-up is reduced by providing notches to inhibit interference caused by misalignment and/or mismatch of adjacent segments.
    Type: Application
    Filed: June 25, 2004
    Publication date: December 29, 2005
    Inventor: Remy Synnott
  • Patent number: 6916154
    Abstract: A resilient ring for sealing between an inner housing surface of revolution and a coaxial outer housing surface of revolution, one of the housing surfaces being a sloped surface with a sloped profile intersecting an axially extending plane and the other housing surface being an axial abutment surface in a substantially radially extending plane. The ring has a circumferential sealing surface for sealing engagement of the ring with the sloped housing surface, and a planar abutment surface for sealing engagement of the ring with the axial abutment housing surface.
    Type: Grant
    Filed: April 29, 2003
    Date of Patent: July 12, 2005
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Remy Synnott
  • Publication number: 20050135920
    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: Application
    Filed: December 17, 2003
    Publication date: June 23, 2005
    Inventors: Remy Synnott, Ricardo Trindade
  • Patent number: 6899518
    Abstract: A cooled turbine shroud segment for a gas turbine engine, having an axially extending shroud ring segment with an inner surface, an outer surface, an upstream flange and a downstream flange. The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate is disposed on the outer surface of the shroud ring between the upstream flange and the downstream flange, with an impingement plenum defined between the impingement plate and the outer surface. Axially extending cooling bores in the ring segment extend between the impingement plenum and an outlet. A trough adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.
    Type: Grant
    Filed: December 23, 2002
    Date of Patent: May 31, 2005
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Terrence Lucas, Dominic Bédard, Amir Daniel, Remy Synnott
  • Publication number: 20040219014
    Abstract: A resilient ring for sealing between an inner housing surface of revolution and a coaxial outer housing surface of revolution, one of the housing surfaces being a sloped surface with a sloped profile intersecting an axially extending plane and the other housing surface being an axial abutment surface in a substantially radially extending plane. The ring has a circumferential sealing surface for sealing engagement of the ring with the sloped housing surface, and a planar abutment surface for sealing engagement of the ring with the axial abutment housing surface.
    Type: Application
    Filed: April 29, 2003
    Publication date: November 4, 2004
    Inventor: Remy Synnott
  • Publication number: 20040120803
    Abstract: A cooled turbine shroud segment for a gas turbine engine, having an axially extending shroud ring segment with an inner surface, an outer surface, an upstream flange and a downstream flange. The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate is disposed on the outer surface of the shroud ring between the upstream flange and the downstream flange, with an impingement plenum defined between the impingement plate and the outer surface. Axially extending cooling bores in the ring segment extend between the impingement plenum and an outlet. A trough adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.
    Type: Application
    Filed: December 23, 2002
    Publication date: June 24, 2004
    Inventors: Terrence Lucas, Dominic Bedard, Amir Daniel, Remy Synnott