Patents by Inventor Mark John Laricchiuta
Mark John Laricchiuta 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: 10683806Abstract: A gas turbine engine defines a radial direction and an axial centerline. The gas turbine engine includes a core turbine engine that defines a core inlet. The core inlet is oriented with respect to the axial centerline and positioned along the radial direction such that the area available to capture foreign object debris is minimized. In one aspect, the gas turbine engine defines a capture ratio less than about 35%, wherein the capture ratio is a ratio of an area between a splitter radius and a tangency radius to an area encompassed by the splitter radius. The splitter radius is defined as a radial distance between the axial centerline and an outer lip of a splitter of the core turbine engine. The tangency radius is defined as a radial distance between the axial centerline and a tangency point, which can be defined at an inner lip of the core inlet.Type: GrantFiled: January 5, 2017Date of Patent: June 16, 2020Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Mark John Laricchiuta
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Patent number: 10677264Abstract: A gas turbine engine includes a fan section having a single-stage fan, a core turbine engine, and a nacelle at least partially surrounding the fan of the fan section and the core turbine engine. The gas turbine engine also includes an outlet guide vane extending between a casing of the core turbine engine and the nacelle. The gas turbine engine is configured to define an acoustic ratio greater than or equal to 2.3, with the acoustic ratio being a ratio of an axial spacing between the trailing edge of the fan blade and the leading edge of the outlet guide vane at a radial location seventy-five percent (75%) along the span of the fan blade to the axial width of the fan blade also at the radial location seventy-five percent (75%) along the span of the fan blade.Type: GrantFiled: October 14, 2016Date of Patent: June 9, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Thomas Ory Moniz, Daniel Robert Dwyer, Mark John Laricchiuta, Jeffrey Donald Clements, Brandon Wayne Miller
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Patent number: 10563516Abstract: A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine and fan blades. Each unitary turbine and fan blade includes a single turbine airfoil, a single fan airfoil positioned radially outward from the single turbine airfoil, and a midspan shroud segment defined between the single turbine airfoil and the single fan airfoil.Type: GrantFiled: July 6, 2016Date of Patent: February 18, 2020Assignee: General Electric CompanyInventors: Mark John Laricchiuta, Thomas Ory Moniz
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Patent number: 10550724Abstract: A gas turbine engine includes a fan section and a core turbine engine operable with the fan section. The gas turbine engine also includes a sump pressurization assembly including a valve, a first duct in airflow communication with the valve and a first pressurized air source, and a second duct in airflow communication with the valve and a second pressurized air source. Further, the sump pressurization assembly includes a supply duct selectively in airflow communication with the first duct and the second duct through the valve. The supply duct is located at least partially inward of a core air flowpath of the core turbine engine for pressurizing a sump of the gas turbine engine.Type: GrantFiled: October 11, 2016Date of Patent: February 4, 2020Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Daniel Robert Dwyer, Mark John Laricchiuta, Jeffrey Donald Clements, Brandon Wayne Miller
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Publication number: 20200011185Abstract: A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine and fan blades. Each unitary turbine and fan blade includes a single turbine airfoil, a single fan airfoil positioned radially outward from the single turbine airfoil, and a midspan shroud segment defined between the single turbine airfoil and the single fan airfoil.Type: ApplicationFiled: August 30, 2019Publication date: January 9, 2020Inventors: Mark John Laricchiuta, Thomas Ory Moniz
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Publication number: 20180216576Abstract: A supersonic turbofan engine includes a fan section having a single-stage fan defining a fan pressure ratio greater than 1.9. The supersonic turbofan engine also includes a core turbine engine defining a core air flowpath. A nacelle at least partially surrounds the fan of the fan section and the core turbine engine. The supersonic turbofan engine defines a bypass ratio, the bypass ratio being greater than or equal to three.Type: ApplicationFiled: October 14, 2016Publication date: August 2, 2018Inventors: Brandon Wayne Miller, Mark John Laricchiuta, Daniel Robert Dwyer, Jeffrey Donald Clements, Kenneth Scheffel, Thomas Ory Moniz
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Publication number: 20180187600Abstract: A gas turbine engine defines a radial direction and an axial centerline. The gas turbine engine includes a core turbine engine that defines a core inlet. The core inlet is oriented with respect to the axial centerline and positioned along the radial direction such that the area available to capture foreign object debris is minimized.Type: ApplicationFiled: January 5, 2017Publication date: July 5, 2018Inventors: Thomas Ory Moniz, Mark John Laricchiuta
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Publication number: 20180106274Abstract: A gas turbine engine includes a fan section having a single-stage fan, a core turbine engine, and a nacelle at least partially surrounding the fan of the fan section and the core turbine engine. The gas turbine engine also includes an outlet guide vane extending between a casing of the core turbine engine and the nacelle. The gas turbine engine is configured to define an acoustic ratio greater than or equal to 2.3, with the acoustic ratio being a ratio of an axial spacing between the trailing edge of the fan blade and the leading edge of the outlet guide vane at a radial location seventy-five percent (75%) along the span of the fan blade to the axial width of the fan blade also at the radial location seventy-five percent (75%) along the span of the fan blade.Type: ApplicationFiled: October 14, 2016Publication date: April 19, 2018Inventors: Thomas Ory Moniz, Daniel Robert Dwyer, Mark John Laricchiuta, Jeffrey Donald Clements, Brandon Wayne Miller
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Publication number: 20180100410Abstract: A gas turbine engine includes a fan section and a core turbine engine operable with the fan section. The gas turbine engine also includes a sump pressurization assembly including a valve, a first duct in airflow communication with the valve and a first pressurized air source, and a second duct in airflow communication with the valve and a second pressurized air source. Further, the sump pressurization assembly includes a supply duct selectively in airflow communication with the first duct and the second duct through the valve. The supply duct is located at least partially inward of a core air flowpath of the core turbine engine for pressurizing a sump of the gas turbine engine.Type: ApplicationFiled: October 11, 2016Publication date: April 12, 2018Inventors: Thomas Ory Moniz, Daniel Robert Dwyer, Mark John Laricchiuta, Jeffrey Donald Clements, Brandon Wayne Miller
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Publication number: 20180010463Abstract: A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine and fan blades. Each unitary turbine and fan blade includes a single turbine airfoil, a single fan airfoil positioned radially outward from the single turbine airfoil, and a midspan shroud segment defined between the single turbine airfoil and the single fan airfoil.Type: ApplicationFiled: July 6, 2016Publication date: January 11, 2018Inventors: Mark John Laricchiuta, Thomas Ory Moniz
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Publication number: 20170314509Abstract: A turbofan assembly that includes a primary turbine section and an aft fan section positioned downstream from the primary turbine section. The primary turbine section includes a bypass duct configured to channel a stream of bypass air therethrough, and a main flow duct configured to discharge a stream of exhaust gas therefrom. The bypass duct and the main flow duct each include a discharge end positioned such that a mixed stream of bypass air and exhaust gas is discharged from the primary turbine section. The aft fan section includes at least one turbine and fan stage including a turbine portion and a fan portion coupled to the turbine portion. The turbine portion is positioned to receive the mixed stream of bypass air and exhaust gas, and the fan portion is positioned radially outward from the turbine portion.Type: ApplicationFiled: April 27, 2016Publication date: November 2, 2017Inventors: Mark John Laricchiuta, Thomas Ory Moniz