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).
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Patent number: 10718214Abstract: 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: GrantFiled: March 9, 2017Date of Patent: July 21, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Bruce David Reynolds, Richard David Conner, Costas Vogiatzis, Timothy Gentry
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Publication number: 20180258770Abstract: 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: ApplicationFiled: March 9, 2017Publication date: September 13, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bruce David Reynolds, Richard David Conner, Costas Vogiatzis, Timothy Gentry
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Publication number: 20110250046Abstract: 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: ApplicationFiled: April 7, 2010Publication date: October 13, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Costas Vogiatzis, Ramakumar Venkata Naga Bommisetty, Jwala Singh
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Patent number: 7484935Abstract: 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: GrantFiled: June 2, 2005Date of Patent: February 3, 2009Assignee: Honeywell International Inc.Inventors: Gregory B. Heitland, Costas Vogiatzis
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Patent number: 7476082Abstract: 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: GrantFiled: August 22, 2005Date of Patent: January 13, 2009Assignee: Honeywell International, Inc.Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
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Publication number: 20080260533Abstract: 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: ApplicationFiled: August 22, 2005Publication date: October 23, 2008Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
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Patent number: 7255530Abstract: 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: GrantFiled: December 8, 2004Date of Patent: August 14, 2007Assignee: Honeywell International Inc.Inventors: Costas Vogiatzis, Nidal A. Ghizawi
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Publication number: 20060275126Abstract: 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: ApplicationFiled: June 2, 2005Publication date: December 7, 2006Inventors: Gregory Heitland, Costas Vogiatzis
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Patent number: 7001143Abstract: 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: GrantFiled: March 5, 2004Date of Patent: February 21, 2006Assignee: Honeywell International, Inc.Inventor: Costas Vogiatzis
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Publication number: 20050220616Abstract: 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: ApplicationFiled: December 8, 2004Publication date: October 6, 2005Inventors: Costas Vogiatzis, Nidal Ghizawi
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Patent number: 6948907Abstract: 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: GrantFiled: May 5, 2003Date of Patent: September 27, 2005Assignee: Honeywell International, Inc.Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
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Publication number: 20040223840Abstract: 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: ApplicationFiled: May 5, 2003Publication date: November 11, 2004Inventors: Costas Vogiatzis, Maitreya Madhyastha, Steven Don Arnold
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Publication number: 20040170495Abstract: 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: ApplicationFiled: March 5, 2004Publication date: September 2, 2004Inventor: Costas Vogiatzis
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Patent number: 6709232Abstract: 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: GrantFiled: September 5, 2002Date of Patent: March 23, 2004Assignee: Honeywell International Inc.Inventor: Costas Vogiatzis
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Publication number: 20040047727Abstract: 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: ApplicationFiled: September 5, 2002Publication date: March 11, 2004Inventor: Costas Vogiatzis