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).
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Patent number: 10982856Abstract: A fuel nozzle for injecting fuel and air into a combustor of a gas turbine engine, the fuel nozzle comprising: an outer component having an outward surface adapted for exposure to a flow of hot gas within the combustor, and an inward surface; an inner component concentrically disposed within the inward surface of outer component along a nozzle axis, the inner component defining an axially extending air flow channel; an air passage bore extending through the outward surface of the outer component and communicating with the air flow channel; and a thermal insulating sleeve disposed within the air passage bore, the sleeve having a sleeve body spaced apart from the outer component by an air gap.Type: GrantFiled: February 1, 2019Date of Patent: April 20, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Saeid Oskooei, Gavin Rohiteswar Kisun, Nadia Cheri Swaby, Roger Neil Antony Francis
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Publication number: 20200248904Abstract: A fuel nozzle for injecting fuel and air into a combustor of a gas turbine engine, the fuel nozzle comprising: an outer component having an outward surface adapted for exposure to a flow of hot gas within the combustor, and an inward surface; an inner component concentrically disposed within the inward surface of outer component along a nozzle axis, the inner component defining an axially extending air flow channel; an air passage bore extending through the outward surface of the outer component and communicating with the air flow channel; and a thermal insulating sleeve disposed within the air passage bore, the sleeve having a sleeve body spaced apart from the outer component by an air gap.Type: ApplicationFiled: February 1, 2019Publication date: August 6, 2020Inventors: Saeid OSKOOEI, Gavin Rohiteswar KISUN, Nadia Cheri SWABY, Roger Neil Antony FRANCIS
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Patent number: 8573516Abstract: 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: GrantFiled: October 10, 2012Date of Patent: November 5, 2013Assignee: Pratt & Whitney Canada Corp.Inventor: Saeid Oskooei
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Patent number: 8572976Abstract: 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: GrantFiled: October 4, 2006Date of Patent: November 5, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Jason Fish, Bhawan B. Patel, Saeid Oskooei
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Patent number: 8308076Abstract: 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: GrantFiled: February 20, 2009Date of Patent: November 13, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Saeid Oskooei
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Patent number: 8042752Abstract: 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: GrantFiled: February 20, 2009Date of Patent: October 25, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Saeid Oskooei, Nicholas Hope
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Patent number: 7926286Abstract: 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: GrantFiled: September 26, 2006Date of Patent: April 19, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Oleg Morenko, Bhawan B. Patel, Nagaraja Rudrapatna, Saeid Oskooei
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Publication number: 20100213290Abstract: 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: ApplicationFiled: February 20, 2009Publication date: August 26, 2010Inventors: Saeid OSKOOEI, Nicholas Hope
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Publication number: 20080083225Abstract: 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: ApplicationFiled: October 4, 2006Publication date: April 10, 2008Inventors: Jason Fish, Bhawan B. Patel, Saeid Oskooei
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Publication number: 20080072599Abstract: 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: ApplicationFiled: September 26, 2006Publication date: March 27, 2008Inventors: Oleg MORENKO, Bhawan B. PATEL, Nagaraja RUDRAPATNA, Saeid OSKOOEI
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Patent number: 6880341Abstract: 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: GrantFiled: December 18, 2002Date of Patent: April 19, 2005Assignee: Pratt & Whitney Canada Corp.Inventors: Kenneth Parkman, Saeid Oskooei
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Patent number: 6871488Abstract: 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: GrantFiled: December 17, 2002Date of Patent: March 29, 2005Assignee: Pratt & Whitney Canada Corp.Inventors: Saeid Oskooei, Kian McCaldon
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Publication number: 20040118121Abstract: 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: ApplicationFiled: December 18, 2002Publication date: June 24, 2004Inventors: Kenneth Parkman, Saeid Oskooei
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Publication number: 20040112061Abstract: 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: ApplicationFiled: December 17, 2002Publication date: June 17, 2004Inventors: Saeid Oskooei, Kian McCaldon
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Patent number: 6536201Abstract: 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: GrantFiled: December 11, 2000Date of Patent: March 25, 2003Assignee: Pratt & Whitney Canada Corp.Inventors: Peter Stuttaford, Bernhard Fischer, David Edwin Cowburn, Saeid Oskooei, Michael Andrew Fryer, Aleksandar Kojovic, Jeffrey Scott Acton
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Publication number: 20020069644Abstract: 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: ApplicationFiled: December 11, 2000Publication date: June 13, 2002Inventors: Peter Stuttaford, Bernhard Fischer, David Edwin Cowburn, Saeid Oskooei, Michael Andrew Fryer, Aleksandar Kojovic, Jeffrey Scott Acton