Patents by Inventor Rajiv Rana
Rajiv Rana 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: 9719362Abstract: A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.Type: GrantFiled: April 24, 2013Date of Patent: August 1, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rajiv Rana, Ardeshir Riahi, Bradley Reed Tucker, David Chou
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Patent number: 9657642Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.Type: GrantFiled: March 27, 2014Date of Patent: May 23, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shezan Kanjiyani, John Gintert, Rajiv Rana, Lorenzo Crosatti, Bradley Reed Tucker, Ed Zurmehly
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Patent number: 9650900Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.Type: GrantFiled: May 7, 2012Date of Patent: May 16, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Malak Fouad Malak, Rajiv Rana, Luis Tapia, David Chou, Jong Liu
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Patent number: 9562437Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.Type: GrantFiled: April 26, 2013Date of Patent: February 7, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel C. Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
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Patent number: 9228440Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.Type: GrantFiled: December 3, 2012Date of Patent: January 5, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel Cregg Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
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Publication number: 20150275763Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.Type: ApplicationFiled: March 27, 2014Publication date: October 1, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shezan Kanjiyani, John Gintert, Rajiv Rana, Lorenzo Crosatti, Bradley Reed Tucker, Ed Zurmehly
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Patent number: 9115586Abstract: An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.Type: GrantFiled: April 19, 2012Date of Patent: August 25, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: David K. Jan, Christopher Zollars, Rajiv Rana, Tom Polakis, Ardeshir Riahi
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Publication number: 20140154096Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.Type: ApplicationFiled: December 3, 2012Publication date: June 5, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel Cregg Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
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Patent number: 8616832Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: GrantFiled: November 30, 2009Date of Patent: December 31, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Publication number: 20130294889Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.Type: ApplicationFiled: May 7, 2012Publication date: November 7, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Malak Fouad Malak, Rajiv Rana, Luis Tapia, David Chou, Jong Liu
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Publication number: 20130280036Abstract: An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.Type: ApplicationFiled: April 19, 2012Publication date: October 24, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: David K. Jan, Christopher Zollars, Rajiv Rana, Tom Polakis, Ardeshir Riahi
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Patent number: 8292581Abstract: An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.Type: GrantFiled: January 9, 2008Date of Patent: October 23, 2012Assignee: Honeywell International Inc.Inventors: Kin C. Poon, Malak F. Malak, Rajiv Rana, Ardeshir Riahi, David H. Chou
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Patent number: 8292587Abstract: A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.Type: GrantFiled: December 18, 2008Date of Patent: October 23, 2012Assignee: Honeywell International Inc.Inventors: Kin Poon, Rajiv Rana, Bob Mitlin, Ardeshir Riahi, David Chou, Steve Halfmann, Frank Mignano
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Publication number: 20110129342Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: ApplicationFiled: November 30, 2009Publication date: June 2, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Publication number: 20100158700Abstract: A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.Type: ApplicationFiled: December 18, 2008Publication date: June 24, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Kin Poon, Rajiv Rana, Bob Mitlin, Ardeshir Riahi, David Chou, Steve Halfmann, Frank Mignano
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Publication number: 20090175733Abstract: An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.Type: ApplicationFiled: January 9, 2008Publication date: July 9, 2009Applicant: Honeywell International, Inc.Inventors: Kin C. Poon, Malak F. Malak, Rajiv Rana, Ardeshir Riahi, David H. Chou