Patents by Inventor Saeid Oskooei

Saeid Oskooei 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: 8573516
    Abstract: A method of designing a fuel nozzle of a gas turbine engine to reduce fretting thereof during use, including establishing an initial nozzle design, determining a first natural frequency of that design and a running frequency range of the gas turbine engine, and increasing a first transverse dimension of the stem member of the nozzle across a length of a portion thereof adjacent the inlet end until the first natural frequency of the nozzle is outside the running range, while a second transverse dimension of the portion remains at least substantially unchanged across the length thereof.
    Type: Grant
    Filed: October 10, 2012
    Date of Patent: November 5, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Saeid Oskooei
  • Patent number: 8572976
    Abstract: A fuel manifold assembly for a gas turbine engine fuel system comprises a fuel manifold at least partly enclosed by a heat shield, the internal manifold being made of a first material having a first coefficient of thermal expansion, and the heat shield being made of a second material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion.
    Type: Grant
    Filed: October 4, 2006
    Date of Patent: November 5, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jason Fish, Bhawan B. Patel, Saeid Oskooei
  • Patent number: 8308076
    Abstract: A method of designing a fuel nozzle of a gas turbine engine to reduce fretting thereof during use, including establishing an initial nozzle design, determining a first natural frequency of that design and a running frequency range of the gas turbine engine, and increasing a first transverse dimension of the stem member of the nozzle across a length of a portion thereof adjacent the inlet end until the first natural frequency of the nozzle is outside the running range, while a second transverse dimension of the portion remains at least substantially unchanged across the length thereof.
    Type: Grant
    Filed: February 20, 2009
    Date of Patent: November 13, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Saeid Oskooei
  • Patent number: 8042752
    Abstract: A method repair for reducing fretting of a fuel nozzle of a gas turbine engine, including attaching at least one stiffening element to an outer surface of a portion of a stem member of the fuel nozzle, with a size and shape of the at least one stiffening element being selected such that a first natural frequency of the fuel nozzle with the at least one stiffening element attached thereto is outside the engine running frequency range.
    Type: Grant
    Filed: February 20, 2009
    Date of Patent: October 25, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Saeid Oskooei, Nicholas Hope
  • Patent number: 7926286
    Abstract: A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, and detachably retained around the manifold ring through a plurality of removable fasteners.
    Type: Grant
    Filed: September 26, 2006
    Date of Patent: April 19, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Oleg Morenko, Bhawan B. Patel, Nagaraja Rudrapatna, Saeid Oskooei
  • Publication number: 20100213290
    Abstract: A method repair for reducing fretting of a fuel nozzle of a gas turbine engine, including attaching at least one stiffening element to an outer surface of a portion of a stem member of the fuel nozzle, with a size and shape of the at least one stiffening element being selected such that a first natural frequency of the fuel nozzle with the at least one stiffening element attached thereto is outside the engine running frequency range.
    Type: Application
    Filed: February 20, 2009
    Publication date: August 26, 2010
    Inventors: Saeid OSKOOEI, Nicholas Hope
  • Publication number: 20080083225
    Abstract: A fuel manifold assembly for a gas turbine engine fuel system comprises a fuel manifold at least partly enclosed by a heat shield, the internal manifold being made of a first material having a first coefficient of thermal expansion, and the heat shield being made of a second material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion.
    Type: Application
    Filed: October 4, 2006
    Publication date: April 10, 2008
    Inventors: Jason Fish, Bhawan B. Patel, Saeid Oskooei
  • Publication number: 20080072599
    Abstract: A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, and detachably retained around the manifold ring through a plurality of removable fasteners.
    Type: Application
    Filed: September 26, 2006
    Publication date: March 27, 2008
    Inventors: Oleg MORENKO, Bhawan B. PATEL, Nagaraja RUDRAPATNA, Saeid OSKOOEI
  • Patent number: 6880341
    Abstract: A floating collar assembly for damping vibration and sealing between a combustor and a fuel nozzle of a gas turbine engine. The combustor has a nozzle opening with an outer peripheral abutment surface and the nozzle is integral with an internal fuel manifold that is secured to the engine core relative to the combustor. The nozzle has a cylindrical body aligned with the nozzle opening and has a shoulder laterally extending from the nozzle body. An annular floating collar has a combustor face adapted for radial sliding engagement with the abutment surface, a central aperture adapted for axial sliding engagement with the cylindrical body and an outer bearing surface. A wave spring is disposed between the outer bearing surface of the floating collar and an inner surface of the nozzle shoulder, for maintaining sealing engagement, for damping vibration, and for impeding relative rotation between the nozzle and the combustor, while accommodating axial and radial relative displacement.
    Type: Grant
    Filed: December 18, 2002
    Date of Patent: April 19, 2005
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kenneth Parkman, Saeid Oskooei
  • Patent number: 6871488
    Abstract: A gas fuel nozzle for mounting in a combustor wall of a gas turbine engine, with an at least partially radially-directed array of gas fuel outlets extending beyond an air flow head having an array of compressed air jet apertures around the gas fuel outlets. The air flow head also has a deflector for creating an axial flow of air for deflecting in an axial direction the radially-injected gas fuel.
    Type: Grant
    Filed: December 17, 2002
    Date of Patent: March 29, 2005
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Saeid Oskooei, Kian McCaldon
  • Publication number: 20040118121
    Abstract: A floating collar assembly for damping vibration and sealing between a combustor and a fuel nozzle of a gas turbine engine. The combustor has a nozzle opening with an outer peripheral abutment surface and the nozzle is integral with an internal fuel manifold that is secured to the engine core relative to the combustor. The nozzle has a cylindrical body aligned with the nozzle opening and has a shoulder laterally extending from the nozzle body. An annular floating collar has a combustor face adapted for radial sliding engagement with the abutment surface, a central aperture adapted for axial sliding engagement with the cylindrical body and an outer bearing surface. A wave spring is disposed between the outer bearing surface of the floating collar and an inner surface of the nozzle shoulder, for maintaining sealing engagement, for damping vibration, and for impeding relative rotation between the nozzle and the combustor, while accommodating axial and radial relative displacement.
    Type: Application
    Filed: December 18, 2002
    Publication date: June 24, 2004
    Inventors: Kenneth Parkman, Saeid Oskooei
  • Publication number: 20040112061
    Abstract: A gas fuel nozzle for mounting in a combustor wall of a gas turbine engine, with an at least partially radially-directed array of gas fuel outlets extending beyond an air flow head having an array of compressed air jet apertures around the gas fuel outlets. The air flow head also has a deflector for creating an axial flow of air for deflecting in an axial direction the radially-injected gas fuel.
    Type: Application
    Filed: December 17, 2002
    Publication date: June 17, 2004
    Inventors: Saeid Oskooei, Kian McCaldon
  • Patent number: 6536201
    Abstract: The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling.
    Type: Grant
    Filed: December 11, 2000
    Date of Patent: March 25, 2003
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Peter Stuttaford, Bernhard Fischer, David Edwin Cowburn, Saeid Oskooei, Michael Andrew Fryer, Aleksandar Kojovic, Jeffrey Scott Acton
  • Publication number: 20020069644
    Abstract: The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling.
    Type: Application
    Filed: December 11, 2000
    Publication date: June 13, 2002
    Inventors: Peter Stuttaford, Bernhard Fischer, David Edwin Cowburn, Saeid Oskooei, Michael Andrew Fryer, Aleksandar Kojovic, Jeffrey Scott Acton