Patents by Inventor Nicholas J. Madonna
Nicholas J. Madonna 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: 11828193Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.Type: GrantFiled: May 4, 2021Date of Patent: November 28, 2023Assignee: RTX CorporationInventors: Nicholas J. Madonna, Daniel P. Preuss, Kristopher K. Anderson
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Publication number: 20230304412Abstract: Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail, wherein the interior platform surface, the forward rail, and the aft rail define a plenum, an airfoil extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity and a baffle installed within the leading edge cavity, and platform feed structure arranged on the platform in the plenum and defining a fluid path through the forward rail and into the baffle of the leading edge cavity.Type: ApplicationFiled: January 30, 2023Publication date: September 28, 2023Inventors: Daniel P. Preuss, Dominic J. Mongillo, Jr., Kristopher K. Anderson, Nicholas J. Madonna
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Patent number: 11225875Abstract: Vane assemblies are described. The vane assemblies include a platform, an airfoil extending from the platform, a forward rail extending from the platform and arranged along a forward side of the platform, and an aft rail extending from the platform and arranged along an aft side of the platform. At least one support beam is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness in a radial direction of 40% or less of a total radial extent from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness in a circumferential direction of 30% or less of a total circumferential extent of vane assembly.Type: GrantFiled: January 27, 2021Date of Patent: January 18, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Nicholas J. Madonna, Kristopher K. Anderson, Justin M. Aniello, Jeffrey Michael Jacques, Daniel P. Preuss, Christina A. Ryan, Melissa Shallcross
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Patent number: 11187092Abstract: A vane for a gas turbine engine, the vane having: an airfoil; and a root portion disposed on a side of the airfoil and including a platform, the platform having a vane forward rail and an extension extending from the platform, the extension defining portions of an outer diameter platform cavity and an airfoil leading edge cavity. The extension extends from the platform such that an upper portion of each of the outer diameter platform cavity and the airfoil leading edge cavity is spaced equidistant from the platform.Type: GrantFiled: May 17, 2019Date of Patent: November 30, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Shawn M. McMahon, Nicholas J. Madonna
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Publication number: 20210270138Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.Type: ApplicationFiled: May 4, 2021Publication date: September 2, 2021Inventors: Nicholas J. Madonna, Daniel P. Preuss, Kristopher K. Anderson
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Patent number: 11078796Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.Type: GrantFiled: December 14, 2018Date of Patent: August 3, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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Patent number: 11073024Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: GrantFiled: December 14, 2018Date of Patent: July 27, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Mohamed Hassan, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher
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Patent number: 11021966Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.Type: GrantFiled: April 24, 2019Date of Patent: June 1, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Nicholas J. Madonna, Daniel P. Preuss, Kristopher K. Anderson
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Patent number: 11008872Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: GrantFiled: December 14, 2018Date of Patent: May 18, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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Publication number: 20200362711Abstract: A vane for a gas turbine engine, the vane having: an airfoil; and a root portion disposed on a side of the airfoil and including a platform, the platform having a vane forward rail and an extension extending from the platform, the extension defining portions of an outer diameter platform cavity and an airfoil leading edge cavity. The extension extends from the platform such that an upper portion of each of the outer diameter platform cavity and the airfoil leading edge cavity is spaced equidistant from the platform.Type: ApplicationFiled: May 17, 2019Publication date: November 19, 2020Inventors: Shawn M. McMahon, Nicholas J. Madonna
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Publication number: 20200340362Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.Type: ApplicationFiled: April 24, 2019Publication date: October 29, 2020Inventors: Nicholas J. Madonna, Daniel P. Preuss, Kristopher K. Anderson
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Publication number: 20200190995Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: United Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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Publication number: 20200190993Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: United Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Mohamed Hassan, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher
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Publication number: 20200190994Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: United Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan