Patents by Inventor Costas Vogiatzis

Costas Vogiatzis 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).

  • Patent number: 10718214
    Abstract: A rotor blade comprises a mount and a blade that extends from the mount along a radial axis. The leading edge includes an indent segment. The leading edge has a leading edge radial length measured along the radial axis. The indent segment has an indent radial length measured along the radial axis. The indent segment has an indent depth. A first ratio of the indent radial length to the leading edge radial length is at most 0.5. A second ratio of the indent depth to the indent radial length is at least 0.05.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: July 21, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Richard David Conner, Costas Vogiatzis, Timothy Gentry
  • Publication number: 20180258770
    Abstract: A rotor blade comprises a mount and a blade that extends from the mount along a radial axis. The leading edge includes an indent segment. The leading edge has a leading edge radial length measured along the radial axis. The indent segment has an indent radial length measured along the radial axis. The indent segment has an indent depth. A first ratio of the indent radial length to the leading edge radial length is at most 0.5. A second ratio of the indent depth to the indent radial length is at least 0.05.
    Type: Application
    Filed: March 9, 2017
    Publication date: September 13, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Richard David Conner, Costas Vogiatzis, Timothy Gentry
  • Publication number: 20110250046
    Abstract: Methods and apparatus are provided for improving engine performance in a turbofan gas turbine engine following foreign object ingestion in turbofan gas turbine engines that include an intake fan that includes a plurality of fan blades, and that is disposed within and surrounded by a fan case. The occurrence of a foreign object ingestion by the turbofan gas turbine engine is detected and, upon detecting that a foreign object has been ingested, air is bled from a region proximate the blades of the intake fan through a slot in the fan case.
    Type: Application
    Filed: April 7, 2010
    Publication date: October 13, 2011
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Costas Vogiatzis, Ramakumar Venkata Naga Bommisetty, Jwala Singh
  • Patent number: 7484935
    Abstract: Disclosed herein is a turbine rotor having a contoured hub comprising a cambered surface extending from a leading edge of the rotor hub to a trailing edge of the rotor hub along an axial direction of the rotor hub. A turbine rotor and a gas turbine engine comprising a turbine rotor flow path having a cambered surface are also disclosed, together with a method providing a turbine rotor flow path for a turbine rotor hub.
    Type: Grant
    Filed: June 2, 2005
    Date of Patent: February 3, 2009
    Assignee: Honeywell International Inc.
    Inventors: Gregory B. Heitland, Costas Vogiatzis
  • Patent number: 7476082
    Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.
    Type: Grant
    Filed: August 22, 2005
    Date of Patent: January 13, 2009
    Assignee: Honeywell International, Inc.
    Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
  • Publication number: 20080260533
    Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.
    Type: Application
    Filed: August 22, 2005
    Publication date: October 23, 2008
    Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
  • Patent number: 7255530
    Abstract: An exemplary vane for a radial turbine assembly includes a hub end and a shroud end that define vane height, a leading edge and a trailing edge that define vane length along a camberline and an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of the vane, vane length and vane thickness vary with respect to vane height. Other exemplary vanes, assemblies, methods, etc., are also disclosed.
    Type: Grant
    Filed: December 8, 2004
    Date of Patent: August 14, 2007
    Assignee: Honeywell International Inc.
    Inventors: Costas Vogiatzis, Nidal A. Ghizawi
  • Publication number: 20060275126
    Abstract: Disclosed herein is a turbine rotor having a contoured hub comprising a cambered surface extending from a leading edge of the rotor hub to a trailing edge of the rotor hub along an axial direction of the rotor hub. A turbine rotor and a gas turbine engine comprising a turbine rotor flow path having a cambered surface are also disclosed, together with a method providing a turbine rotor flow path for a turbine rotor hub.
    Type: Application
    Filed: June 2, 2005
    Publication date: December 7, 2006
    Inventors: Gregory Heitland, Costas Vogiatzis
  • Patent number: 7001143
    Abstract: Improved cambered vanes comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, having a gradually curved section and a substantially flat section.
    Type: Grant
    Filed: March 5, 2004
    Date of Patent: February 21, 2006
    Assignee: Honeywell International, Inc.
    Inventor: Costas Vogiatzis
  • Publication number: 20050220616
    Abstract: An exemplary vane for a radial turbine assembly includes a hub end and a shroud end that define vane height, a leading edge and a trailing edge that define vane length along a camberline and an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of the vane, vane length and vane thickness vary with respect to vane height. Other exemplary vanes, assemblies, methods, etc., are also disclosed.
    Type: Application
    Filed: December 8, 2004
    Publication date: October 6, 2005
    Inventors: Costas Vogiatzis, Nidal Ghizawi
  • Patent number: 6948907
    Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.
    Type: Grant
    Filed: May 5, 2003
    Date of Patent: September 27, 2005
    Assignee: Honeywell International, Inc.
    Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
  • Publication number: 20040223840
    Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.
    Type: Application
    Filed: May 5, 2003
    Publication date: November 11, 2004
    Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
  • Publication number: 20040170495
    Abstract: Improved cambered vanes comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, having a gradually curved section and a substantially flat section.
    Type: Application
    Filed: March 5, 2004
    Publication date: September 2, 2004
    Inventor: Costas Vogiatzis
  • Patent number: 6709232
    Abstract: Improved cambered vanes are constructed for use within a vaned turbocharger and comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane inner and outer airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, that has a gradually curved section and a substantially flat section.
    Type: Grant
    Filed: September 5, 2002
    Date of Patent: March 23, 2004
    Assignee: Honeywell International Inc.
    Inventor: Costas Vogiatzis
  • Publication number: 20040047727
    Abstract: Improved cambered vanes of this invention are constructed for use within a vaned turbocharger and comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane inner and outer airfoil surfaces, in conjunction with the vane leading edge, are specially configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, that has a gradually curved section and a substantially flat section.
    Type: Application
    Filed: September 5, 2002
    Publication date: March 11, 2004
    Inventor: Costas Vogiatzis