Patents by Inventor Jorge Francisco Seda
Jorge Francisco Seda 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: 8091334Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: GrantFiled: January 26, 2011Date of Patent: January 10, 2012Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Patent number: 8016561Abstract: A method for operating a turbofan engine includes providing a first fan disk configured to rotate in a first rotational direction, coupling a first fan blade to the first fan disk, the first fan blade including a dovetail, an airfoil coupled to the dovetail, and a plurality of channels extending through the dovetail, and channeling airflow through the at least one fan blade such that the airflow is discharged from the airfoil trailing edge to facilitate reducing the operational noise level of the turbofan engine and improve.Type: GrantFiled: July 11, 2006Date of Patent: September 13, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Justin Paul Stephenson
-
Publication number: 20110120136Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: ApplicationFiled: January 26, 2011Publication date: May 26, 2011Inventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Patent number: 7886518Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: GrantFiled: November 14, 2006Date of Patent: February 15, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Patent number: 7726116Abstract: A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other defining an annular fan bypass duct. A first member couples the nacelle to the core cowl and includes a first flap hingedly coupled to each sidewall of the first member. An opposing second member couples the nacelle to the core cowl and includes a second flap hingedly coupled to each sidewall of the second member. The first flaps and the second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct. A turbofan engine assembly and a method for operating the same are also provided.Type: GrantFiled: November 14, 2006Date of Patent: June 1, 2010Assignee: General Electric CompanyInventors: Paul D. Kemper, Thomas Ory Moniz, Jorge Francisco Seda
-
Patent number: 7681399Abstract: A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.Type: GrantFiled: November 14, 2006Date of Patent: March 23, 2010Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz, Jorge Francisco Seda
-
Patent number: 7673458Abstract: A method for operating a turbofan engine assembly including a core gas turbine engine is provided. The method includes varying an operating speed of the turbofan engine assembly from a first operating speed to a second operating speed. The method also includes selectively positioning a first arcuate portion and a second arcuate portion of a split cowl assembly to vary a throat area of a fan nozzle duct defined downstream from the core gas turbine engine to facilitate improving engine efficiency at the second operating speed. The split cowl assembly is downstream from the core gas turbine engine and inside the fan nozzle duct. A turbofan engine assembly and nozzle assembly are also provided.Type: GrantFiled: November 14, 2006Date of Patent: March 9, 2010Assignee: General Electric CompanyInventors: Paul D. Kemper, Thomas Ory Moniz, Jorge Francisco Seda
-
Patent number: 7673442Abstract: A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed.Type: GrantFiled: November 14, 2006Date of Patent: March 9, 2010Assignee: General Electric CompanyInventors: Jorge Francisco Seda, Thomas Ory Moniz, Robert Joseph Orlando, Alan Roy Stuart, Kenneth S. Scheffel
-
Publication number: 20080112801Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: ApplicationFiled: November 14, 2006Publication date: May 15, 2008Inventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Publication number: 20080110152Abstract: A method for operating a turbofan engine assembly including a core gas turbine engine is provided. The method includes varying an operating speed of the turbofan engine assembly from a first operating speed to a second operating speed. The method also includes selectively positioning a first arcuate portion and a second arcuate portion of a split cowl assembly to vary a throat area of a fan nozzle duct defined downstream from the core gas turbine engine to facilitate improving engine efficiency at the second operating speed. The split cowl assembly is downstream from the core gas turbine engine and inside the fan nozzle duct. A turbofan engine assembly and nozzle assembly are also provided.Type: ApplicationFiled: November 14, 2006Publication date: May 15, 2008Inventors: Paul D. Kemper, Thomas Ory Moniz, Jorge Francisco Seda
-
Publication number: 20080112802Abstract: A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.Type: ApplicationFiled: November 14, 2006Publication date: May 15, 2008Inventors: Robert Joseph Orlando, Thomas Ory Moniz, Jorge Francisco Seda
-
Publication number: 20080110154Abstract: A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other defining an annular fan bypass duct. A first member couples the nacelle to the core cowl and includes a first flap hingedly coupled to each sidewall of the first member. An opposing second member couples the nacelle to the core cowl and includes a second flap hingedly coupled to each sidewall of the second member. The first flaps and the second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct. A turbofan engine assembly and a method for operating the same are also provided.Type: ApplicationFiled: November 14, 2006Publication date: May 15, 2008Inventors: Paul D. Kemper, Thomas Ory Moniz, Jorge Francisco Seda
-
Publication number: 20080110153Abstract: A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed.Type: ApplicationFiled: November 14, 2006Publication date: May 15, 2008Inventors: Jorge Francisco Seda, Thomas Ory Moniz, Robert Joseph Orlando, Alan Roy Stuart, Kenneth S. Scheffel
-
Publication number: 20080014095Abstract: A method for operating a turbofan engine includes providing a first fan disk configured to rotate in a first rotational direction, coupling a first fan blade to the first fan disk, the first fan blade including a dovetail, an airfoil coupled to the dovetail, and a plurality of channels extending through the dovetail, and channeling airflow through the at least one fan blade such that the airflow is discharged from the airfoil trailing edge to facilitate reducing the operational noise level of the turbofan engine and improve.Type: ApplicationFiled: July 11, 2006Publication date: January 17, 2008Inventors: Thomas Ory Moniz, Jorge Francisco Seda, Justin Paul Stephenson
-
Patent number: 7195446Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.Type: GrantFiled: October 29, 2004Date of Patent: March 27, 2007Assignee: General Electric CompanyInventors: Jorge Francisco Seda, Thomas Ory Moniz, Lawrence Butler