Patents by Inventor Ian Tibbott

Ian Tibbott 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).

  • Heat transfer promotion structure for internally convectively cooled airfoils
    Patent number: 6406260
    Abstract: A cooled airfoil has an internal cooling passage in which a plurality of trip strips are arranged to effect variable coolant flow and heat transfer coefficient distribution so as to advantageously minimize the amount of coolant flow required to adequately cool the airfoil structure. In one embodiment, this is accomplished by varying the dimensions of the trip strips along a transversal axis relative to the cooling passage.
    Type: Grant
    Filed: October 22, 1999
    Date of Patent: June 18, 2002
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ricardo Trindade, Michael Papple, William Abdel-Messeh, Ian Tibbott
  • Cast airfoil structure with openings which do not require plugging
    Patent number: 6257831
    Abstract: A cooled gas turbine engine airfoil comprises a flow deflector arrangement adapted to re-direct a cooling fluid away from an unfilled opening left by a support member of a casting core used during the casting of the airfoil. The provision of the flow deflector arrangement advantageously allows for a larger core support, thereby facilitating the manufacture of the airfoil.
    Type: Grant
    Filed: October 22, 1999
    Date of Patent: July 10, 2001
    Assignee: Pratt & whitney Canada Corp.
    Inventors: Michael Papple, William Abdel-Messeh, Ian Tibbott
  • Cooling passages for airfoil leading edge
    Patent number: 5779437
    Abstract: A cooling structure for the leading edge area of an airfoil having a plurality of passages wherein each passage has a radial component and a downstream component relative to the leading edge axis, and the outlet of each passage has a diffuser area formed by conical machining, wherein the diffuser area is recessed in the wall portion downstream of the passage.
    Type: Grant
    Filed: October 31, 1996
    Date of Patent: July 14, 1998
    Assignee: Pratt & Whitney Canada Inc.
    Inventors: William Abdel-Messeh, Ian Tibbott, Subhash Arora
  • Gas turbine airfoil cooling
    Patent number: 5711650
    Abstract: A cooling system for airfoil vanes in a turbine of a gas turbine engine wherein the airfoil platforms have openings downstream of the insert tube for passing spent platform impingement coolant air into the airfoil cavity downstream of the insert tube to increase the pressure in the aft zone of the airfoil to improve the temperature gradient across the span of the airfoil.
    Type: Grant
    Filed: October 4, 1996
    Date of Patent: January 27, 1998
    Assignee: Pratt & Whitney Canada, Inc.
    Inventors: Ian Tibbott, William Abdel-Messeh, Michael Papple
  • 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