Patents by Inventor Tracy A. Propheter-Hinckley

Tracy A. Propheter-Hinckley 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: 11371390
    Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a composite gas turbine engine component including a first flange extending radially from a main body at a junction having an arcuate profile. An adapter ring includes a mate face dimensioned to follow a contour of the junction such that the junction sits on the mate face. A method of assembly for a gas turbine engine is also disclosed.
    Type: Grant
    Filed: April 23, 2020
    Date of Patent: June 28, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jonas S. Banhos, Tracy A. Propheter-Hinckley
  • Patent number: 11339718
    Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: May 24, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Patent number: 11339667
    Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: August 11, 2020
    Date of Patent: May 24, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: San Quach, Bryan P. Dube, Tracy A. Propheter-Hinckley, Allan N. Arisi, Adam P. Generale, Lucas Dvorozniak, Howard J. Liles
  • Patent number: 11333023
    Abstract: A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: May 17, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Patent number: 11333036
    Abstract: An article includes a ceramic matrix composite wall that defines at least a side of a passage. The ceramic wall includes a ceramic matrix composite flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. The ceramic matric composite of the wall comprises woven fibers that are dispersed in a ceramic body matrix. An airfoil and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: August 30, 2019
    Date of Patent: May 17, 2022
    Assignee: RAYTHEON TECHNOLOGIES
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 11319817
    Abstract: An airfoil includes a core structure that defines a cooling passage and first and second panels that are attached with the core structure. Each of the first and second panels includes an exterior gas path side, an opposed interior side, and a side edge. The side edge has a bearing portion that defines a bearing surface. The bearing surface of the first panel abuts the bearing surface of the second panel at a bearing interface. There are channels in the bearing portion of the first panel. Each of the channels has a first end that opens to the cooling passage and a second end that opens to the exterior gas path side at one of the side edges. Each of the channels is defined on a side by the bearing surface of the second panel.
    Type: Grant
    Filed: March 17, 2020
    Date of Patent: May 3, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 11293347
    Abstract: An airfoil has a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib extends from the first side to the second side and partitions an internal core cavity into a forward cavity and an aft cavity. A baffle is disposed in the forward cavity and has a showerhead array of impingement orifices adjacent the leading end of the airfoil wall. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall, an array of pedestals, and at least one outlet orifice through the outer portion. The inlet orifice opens to the forward cavity at a location aft of the showerhead array of impingement orifices.
    Type: Grant
    Filed: October 30, 2019
    Date of Patent: April 5, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Allan N. Arisi
  • Patent number: 11286790
    Abstract: A gas turbine engine component includes a wall that has an inner surface and an outer surface. An inlet is defined by the inner surface. At least one non-rectangular slot is defined by the outer surface and includes at least one protrusion extending into the slot. A slot passage fluidly connects the inlet to the at least one non-rectangular slot. The slot passage comprises an inlet portion that extends through the wall from the inlet to an intermediate portion. An outlet portion extends through the wall from the intermediate portion to the at least one non-rectangular slot.
    Type: Grant
    Filed: September 2, 2020
    Date of Patent: March 29, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: San Quach, Christopher King, Tracy A. Propheter-Hinckley
  • Patent number: 11268387
    Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.
    Type: Grant
    Filed: January 4, 2019
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: San Quach, Tracy A. Propheter-Hinckley, Dominic J. Mongillo, Jr., Steven Bruce Gautschi
  • Publication number: 20220049608
    Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.
    Type: Application
    Filed: August 11, 2020
    Publication date: February 17, 2022
    Inventors: San Quach, Bryan P. Dube, Tracy A. Propheter-Hinckley, Allan N. Arisi, Adam P. Generale, Lucas Dvorozniak, Howard J. Liles
  • Patent number: 11248470
    Abstract: An airfoil includes an airfoil section that has an airfoil wall that define leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. The airfoil section extends form a platform. The platform defines a shelf that extends forward from the first end at the leading end of the airfoil section to a platform leading edge, aft from the first end at the trailing end of the airfoil section to a platform trailing edge, laterally from the first end at the first side of the airfoil section to a first platform side edge, and laterally from the first end at the second side of the airfoil section to a second platform side edge. The internal core cavity extends from the airfoil section into the shelf.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: February 15, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Allan N. Arisi
  • Publication number: 20220042417
    Abstract: A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.
    Type: Application
    Filed: April 23, 2020
    Publication date: February 10, 2022
    Inventors: Allan N. Arisi, Dominic J. Mongillo, Tracy A. Propheter-Hinckley
  • Patent number: 11242768
    Abstract: A gas turbine engine article includes an article wall that defines a cavity, a cooling passage network embedded between inner and outer portions of the article wall, and at least one conical passage through at least a portion of the inner portion of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, an outlet orifice through the outer portion of the article wall, and an intermediate region of passages that connects the inlet orifice to the outlet orifice. The conical passage has a first end that is proximate the cavity and a second end that opens at the intermediate region of passages.
    Type: Grant
    Filed: March 11, 2020
    Date of Patent: February 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Publication number: 20220003166
    Abstract: A gas turbine engine article includes a baffle that is configured to be mounted in a cavity of a gas turbine engine component. The baffle has a baffle wall that circumscribes an open interior region. The baffle wall includes a forward wall, side walls, and an aft wall. The side walls include impingement orifices, and the aft wall defines two datum features. At least one of the datum features is a dimple that is a portion of a sphere.
    Type: Application
    Filed: September 21, 2021
    Publication date: January 6, 2022
    Inventors: Scott A. Kovach, Tracy A. Propheter-Hinckley
  • Publication number: 20220003120
    Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
    Type: Application
    Filed: September 23, 2021
    Publication date: January 6, 2022
    Inventors: San Quach, Tracy A. Propheter-Hinckley, Steven Bruce Gautschi
  • Publication number: 20210402465
    Abstract: A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.
    Type: Application
    Filed: June 29, 2021
    Publication date: December 30, 2021
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 11203981
    Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a pressure and suction side walls and an internal rib and defining a cavity between, at least, the pressure side wall, the suction side wall, and the internal rib. A baffle insert is arranged within the cavity and includes a sealing portion arranged adjacent to the internal rib of the airfoil body with a gap therebetween. A seal element is arranged within the cavity and located in the gap. The seal element is free to move relative to each of the baffle insert and the airfoil body within the gap. When a pressure differential exists across the seal element, the seal element will sealingly engage between sealing portion of the baffle insert and the internal rib of the airfoil body to block a flow through the gap.
    Type: Grant
    Filed: August 6, 2020
    Date of Patent: December 21, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Allan N. Arisi
  • Patent number: 11203939
    Abstract: An airfoil includes an airfoil section and a platform from which the airfoil section extends. The platform defines a shelf that extends from the airfoil section to a platform edge. The shelf includes a plenum and a plurality of cooling orifices extend from the plenum toward the platform edge. Each of the cooling orifices has a first orifice end that opens to the plenum and a second, closed orifice end adjacent the platform edge.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: December 21, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Publication number: 20210381387
    Abstract: A method for forming a passage in a ceramic matrix composite component incudes forming a core for a ceramic matrix composite component; embedding a hollow member into the core at a desired location for a passage in the ceramic matrix composite component; wrapping the core with a ceramic material; and inserting a rod through the hollow member and into the core.
    Type: Application
    Filed: August 18, 2021
    Publication date: December 9, 2021
    Applicant: Raytheon Technologies Corporation
    Inventors: Tracy A. Propheter-Hinckley, Raymond C. Surace
  • Patent number: 11180998
    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. First and second platforms are attached, respectively, with the first and second ends. A cooling passage circuit extends at least in the first platform and the airfoil section. The cooling passage circuit includes a first plenum in the first platform adjacent at least the first side of the airfoil wall, a hybrid skin core passage embedded in the first side of the airfoil wall and that extends longitudinally, and a resupply passage that connects the first plenum with the hybrid skin core passage.
    Type: Grant
    Filed: August 6, 2019
    Date of Patent: November 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Dominic J. Mongillo, Tracy A. Propheter-Hinckley