Patents by Inventor Matthew A. Devore
Matthew A. Devore 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: 12055056Abstract: An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.Type: GrantFiled: June 17, 2022Date of Patent: August 6, 2024Assignee: RTX CORPORATIONInventors: Brian T. Hazel, John R. Farris, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Paul M. Lutjen, Mario P. Bochiechio
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Patent number: 12037912Abstract: An advanced passive clearance control (APCC) control ring is provided. The APCC control ring includes first and second cover sections, first and second wall sections and a control ring. At least one of the first and second cover sections is bonded to corresponding edges of the first and second wall sections by field assisted sintering technology (FAST) processing along a bond surface to form an enclosure for the control ring.Type: GrantFiled: June 17, 2022Date of Patent: July 16, 2024Assignee: RTX CORPORATIONInventors: Paul M. Lutjen, John R. Farris, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Mario P. Bochiechio, Brian T. Hazel
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Publication number: 20230323784Abstract: An advanced passive clearance control (APCC) control ring is provided. The APCC control ring includes first and second cover sections, first and second wall sections and a control ring. At least one of the first and second cover sections is bonded to corresponding edges of the first and second wall sections by field assisted sintering technology (FAST) processing along a bond surface to form an enclosure for the control ring.Type: ApplicationFiled: June 17, 2022Publication date: October 12, 2023Inventors: Paul M. Lutjen, John R. Farris, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Mario P. Bochiechio, Brian T. Hazel
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Publication number: 20230151738Abstract: A method of assembling a part is provided and includes forming a first section of the part, defining, in the first section, passages with dimensions as small as 0.005 inches (0.127 mm), forming a second section of the part, metallurgically bonding the first and second sections whereby the passages are delimited by the first and second sections and executing the metallurgically bonding without modifying a condition of the passages.Type: ApplicationFiled: June 17, 2022Publication date: May 18, 2023Inventors: Paul M. Lutjen, John R. Farris, Brian T. Hazel, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Mario P. Bochiechio
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Publication number: 20230151736Abstract: A method of repair of a part is provided and includes removing a section that is damaged from the part, casting a replacement section for the part, the replacement section having a geometry similar to that of the section in an undamaged condition and bonding the replacement section to the part using field assisted sintering technology (FAST).Type: ApplicationFiled: June 17, 2022Publication date: May 18, 2023Inventors: Brian T. Hazel, John R. Farris, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Paul M. Lutjen, Mario P. Bochiechio
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Publication number: 20220403742Abstract: An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.Type: ApplicationFiled: June 17, 2022Publication date: December 22, 2022Inventors: Brian T. Hazel, John R. Farris, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Paul M. Lutjen, Mario P. Bochiechio
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Publication number: 20220403755Abstract: An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.Type: ApplicationFiled: June 17, 2022Publication date: December 22, 2022Inventors: Brian T. Hazel, John R. Farris, Matthew A. Devore, John A. Sharon, James F. Wiedenhoefer, Paul M. Lutjen, Mario P. Bochiechio
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Patent number: 11492912Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span.Type: GrantFiled: January 10, 2020Date of Patent: November 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Carey Clum, Matthew A. Devore
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Patent number: 11391523Abstract: A cast plate heat exchanger includes an inner surface of a passage with a first group of augmentation features with a first density across the inner surface. An outer surface includes a second inlet end and a second group of augmentation features arranged with a second density across the outer surface. The first density and second density of augmentation features are located in a targeted manner to reduce thermal stresses.Type: GrantFiled: February 15, 2019Date of Patent: July 19, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William P. Stillman, Michael A. Disori, Matthew A. Devore, Dave J. Hyland, Adam J. Diener
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Patent number: 11143038Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge.Type: GrantFiled: February 26, 2014Date of Patent: October 12, 2021Assignee: Raytheon Technologies CorporationInventors: San Quach, Matthew A. Devore
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Patent number: 10947854Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.Type: GrantFiled: February 18, 2020Date of Patent: March 16, 2021Assignee: Raytheon Technologies CorporationInventors: San Quach, Atul Kohli, Matthew A. Devore, Steven Bruce Gautschi
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Patent number: 10947853Abstract: A gas turbine engine component includes an airfoil that has a leading edge and extends from a first side of a platform that has a leading edge overhang. A root portion extends from a second side of the platform opposite the first side. A cooling passage extends through the platform and beneath a trailing edge of the airfoil. The cooling passage includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the leading edge of the airfoil and the inlet is located axially upstream of the root portion in the leading edge overhang.Type: GrantFiled: September 25, 2019Date of Patent: March 16, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Matthew A. Devore, Matthew S. Gleiner
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Patent number: 10934845Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber. A tangential onboard injector (TOBI) may be disposed in the first airflow path. A radial onboard injector (ROBI) may be disposed in the second airflow path.Type: GrantFiled: February 19, 2020Date of Patent: March 2, 2021Assignee: Raytheon Technologies CorporationInventors: Matthew A Devore, Jonathan Ortiz
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Patent number: 10808554Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.Type: GrantFiled: November 17, 2016Date of Patent: October 20, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Tracy A. Propheter-Hinckley, Michael G. McCaffrey, Raymond Surace, Matthew A. Devore
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Patent number: 10808571Abstract: A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge.Type: GrantFiled: June 22, 2017Date of Patent: October 20, 2020Assignee: Raytheon Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Matthew A. Devore, Renee J. Behlman
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Patent number: 10808551Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.Type: GrantFiled: April 29, 2019Date of Patent: October 20, 2020Assignee: United Technologies CorporationInventors: Eric A. Hudson, Tracy A. Propheter-Hinckley, San Quach, Matthew A. Devore
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Publication number: 20200277861Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.Type: ApplicationFiled: January 10, 2020Publication date: September 3, 2020Inventors: Brandon W. Spangler, Carey Clum, Matthew A. Devore
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Patent number: 10738619Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.Type: GrantFiled: January 2, 2015Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventors: Lane Thornton, Matthew A. Devore, Dominic J. Mongillo, Steven Bruce Gautschi
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Patent number: 10718213Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber.Type: GrantFiled: April 10, 2017Date of Patent: July 21, 2020Assignee: United Technologies CorporationInventors: Matthew A Devore, Jonathan Ortiz
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Patent number: 10711624Abstract: An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.Type: GrantFiled: November 17, 2016Date of Patent: July 14, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Matthew A. Devore, Adam P. Generale, Tracy A. Propheter-Hinckley