Patents by Inventor Brett Alan Bartling
Brett Alan Bartling 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: 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: 11053808Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.Type: GrantFiled: February 14, 2020Date of Patent: July 6, 2021Assignee: Raytheon Technologies CorporationInventors: Russell J. Bergman, Charles C. Wu, Brett Alan Bartling
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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: 20200200027Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.Type: ApplicationFiled: February 14, 2020Publication date: June 25, 2020Inventors: Russell J. Bergman, Charles C. Wu, Brett Alan Bartling
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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: 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: 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
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Patent number: 10641102Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.Type: GrantFiled: October 23, 2017Date of Patent: May 5, 2020Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Christopher Whitfield, Kristopher K. Anderson, Jason B. Moran, Brett Alan Bartling, Christopher Perron, Justin M. Aniello, Stephanie Tanner, Dominic J. Mongillo, Jr.
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Patent number: 10641117Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.Type: GrantFiled: November 6, 2014Date of Patent: May 5, 2020Assignee: United Technologies CorporationInventors: Russell J. Bergman, Charles C. Wu, Brett Alan Bartling
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Patent number: 10352182Abstract: A stator for a gas turbine engine includes a stator vane, a first cooling passage located at the stator to provide a cooling fluid flow to a first portion of the stator, and a second cooling passage located at the stator to provide a cooling fluid flow to a second portion of the stator. A connection passage extends at least partially through the stator to connect a first cooling passage inlet of the first cooling passage to a second cooling passage inlet of the second cooling passage. The cooling fluid flow is directed from a common cooling flow source into the first cooling passage and the second cooling passage via the first cooling passage inlet.Type: GrantFiled: May 20, 2016Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Russell J. Bergman, Brett Alan Bartling
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Publication number: 20190071979Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.Type: ApplicationFiled: October 23, 2017Publication date: March 7, 2019Inventors: Shawn M. McMahon, Christopher Whitfield, Kristopher K. Anderson, Jason B. Moran, Brett Alan Bartling, Christopher Perron, Justin M. Aniello, Stephanie Tanner, Dominic J. Mongillo, JR.
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Publication number: 20190071978Abstract: A vane cluster for a gas turbine engine including an inner diameter platform and an outer diameter platform. A plurality of vanes span from the inner diameter platform to the outer diameter platform. An inbound region is defined between a first vane and a second vane of the plurality of vanes. A plenum is defined in the inner diameter platform at the inbound region. The plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath. A feed hole connects the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.Type: ApplicationFiled: October 23, 2017Publication date: March 7, 2019Inventors: Shawn M. McMahon, Christopher Whitfield, Kristopher K. Anderson, Jason B. Moran, Brett Alan Bartling, Christopher Perron, Justin M. Aniello, Stephanie Tanner
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Publication number: 20170335700Abstract: A stator for a gas turbine engine includes a stator vane, a first cooling passage located at the stator to provide a cooling fluid flow to a first portion of the stator, and a second cooling passage located at the stator to provide a cooling fluid flow to a second portion of the stator. A connection passage extends at least partially through the stator to connect a first cooling passage inlet of the first cooling passage to a second cooling passage inlet of the second cooling passage. The cooling fluid flow is directed from a common cooling flow source into the first cooling passage and the second cooling passage via the first cooling passage inlet.Type: ApplicationFiled: May 20, 2016Publication date: November 23, 2017Inventors: Russell J. Bergman, Brett Alan Bartling
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Publication number: 20160312631Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.Type: ApplicationFiled: November 6, 2014Publication date: October 27, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Russell J. Bergman, Charles C. Wu, Brett Alan Bartling