Patents by Inventor Tracy A. Propheter

Tracy A. Propheter 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).

  • Mini core passage with protrusion
    Patent number: 11092017
    Abstract: An airfoil includes an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The airfoil wall circumscribes an internal core cavity. 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 to receive cooling air from the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The outer portion of the airfoil wall has a protrusion in the cooling passage network that faces toward the inlet orifice.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: August 17, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Allan N. Arisi
  • Airfoil with dual profile leading end
    Patent number: 11092016
    Abstract: An airfoil includes first and second endwalls and an airfoil section having a dual airfoil profile. The airfoil section includes a double wall that has an outer wall that defines a primary leading end of the dual airfoil profile and an inner wall spaced from the outer wall. The outer wall is trapped between the first and second endwalls in mortise and tenon joints, and the inner wall defines a secondary leading end of the dual airfoil profile.
    Type: Grant
    Filed: October 1, 2019
    Date of Patent: August 17, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Turbine engine cooling system with an open loop circuit
    Patent number: 11085325
    Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
    Type: Grant
    Filed: July 12, 2018
    Date of Patent: August 10, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael F. Blair, Tracy A. Propheter-Hinckley, Mark F. Zelesky
  • Method and casting core for forming a landing for welding a baffle inserted in an airfoil
    Patent number: 11077494
    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: Grant
    Filed: July 29, 2016
    Date of Patent: August 3, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Airfoils and core assemblies for gas turbine engines and methods of manufacture
    Patent number: 11041395
    Abstract: Methods for forming airfoils, core assemblies, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly configured to define one or more internal cavities of the airfoil body, the core assembly comprising at least core structure having a purge slot protrusion extending from a portion of the core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: June 22, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Emma J. Place, Timothy J. Jennings, Jeremy B. Fredette
  • Airfoil with cooling passage circuit through platforms and airfoil section
    Patent number: 11028700
    Abstract: An airfoil includes a cooling passage circuit that has a first plenum, a skincore passage, a first connector passage, a second plenum, and a second connector passage. The first plenum is in a first platform and extends adjacent a first side, a trailing end, and a second side of and airfoil section. The skincore passage is embedded in the first side of the airfoil section and extends longitudinally. The first connector passage is longitudinally spaced from an internal core cavity in the airfoil section so as to extend around the cavity. The first connector passage connects the first plenum with the skincore passage. The second plenum is in the second platform and extends adjacent the first side, the trailing end, and the second side of the airfoil section. The second connector passage connects the skincore passage with the second plenum.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: June 8, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Airfoil with cooling passage network having flow guides
    Patent number: 11028702
    Abstract: An airfoil includes a cooling passage network is embedded in an airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an entrance region adjacent the first end of the airfoil section, a plenum region between the entrance region and the second end of the airfoil section, and an exit region adjacent the plenum region. The entrance region includes a plurality of flow guides that divide the entrance region into a plurality of channels that open into the plenum region. The plenum region includes a plurality of pedestals that have a shape that is different from the flow guides.
    Type: Grant
    Filed: December 13, 2018
    Date of Patent: June 8, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Allan N. Arisi
  • NEEDLED CERAMIC MATRIX COMPOSITE COOLING PASSAGES
    Publication number: 20210163365
    Abstract: A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.
    Type: Application
    Filed: September 14, 2020
    Publication date: June 3, 2021
    Applicant: Raytheon Technologies Corporation
    Inventor: Tracy A. Propheter-Hinckley
  • Core assembly including studded spacer
    Patent number: 11014145
    Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: May 25, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, James T. Auxier, Eric A. Hudson
  • MINICORE COOLING PASSAGE NETWORK HAVING SLOPED IMPINGEMENT SURFACE
    Publication number: 20210148236
    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 network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.
    Type: Application
    Filed: October 30, 2019
    Publication date: May 20, 2021
    Inventors: Corneil S. Paauwe, Tracy A. Propheter-Hinckley, Allan N. Arisi
  • Passive centrifugal bleed valve system for a gas turbine engine
    Patent number: 11008979
    Abstract: A passive centrifugal valve for a gas turbine engine. The passive centrifugal valve includes an inner section with a flow control inlet orifice, a cantilevered valve adjacent to the flow control inlet orifice, and an outer section with a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice.
    Type: Grant
    Filed: May 29, 2019
    Date of Patent: May 18, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael G. McCaffrey, Tracy A. Propheter-Hinckley
  • Balance bracket
    Patent number: 11002153
    Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: May 11, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Alberto A. Mateo, Tracy A. Propheter-Hinckley, San Quach
  • Investment casting core system
    Patent number: 10987727
    Abstract: An investment casting core system includes first and second investment casting cores. The first investment casting core has a pin and the second investment casting core has a hole and an access slot that opens to the hole. The pin is disposed in the hole such as to space the first investment casting core in a fixed position relative to the second investment casting core. A bonding agent is disposed in the access slot and around the pin in the hole.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: April 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Chordal seal
    Patent number: 10968777
    Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Kyle J. Brevick
  • Airfoil having impingement leading edge
    Patent number: 10968753
    Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Carey Clum, Timothy J. Jennings
  • Turbine airfoil with minicore passage having sloped diffuser orifice
    Patent number: 10968752
    Abstract: A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.
    Type: Grant
    Filed: April 2, 2019
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: James Tilsley Auxier, Tracy A. Propheter-Hinckley, Allan N. Arisi
  • MULTI-FLOW COOLING CIRCUIT FOR GAS TURBINE ENGINE FLOWPATH COMPONENT
    Publication number: 20210095596
    Abstract: A flowpath component for a gas turbine engine includes a body having a leading edge and a trailing edge. A first exterior wall connects the leading edge to the trailing edge and a second exterior wall connects the leading edge to the trailing edge. At least one first internal cooling passage has a first inlet at a first end of the body. At least one second internal cooling passage has a second inlet at a second end of the body. The at least one first internal cooling passage is isolated from the at least one second internal cooling passage.
    Type: Application
    Filed: September 30, 2019
    Publication date: April 1, 2021
    Inventors: Renee Behlman, Tracy Propheter-Hinckley, Raymond Surace, Matthew Devore
  • AIRFOIL HAVING IMPINGEMENT LEADING EDGE
    Publication number: 20210079793
    Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.
    Type: Application
    Filed: August 27, 2019
    Publication date: March 18, 2021
    Inventors: Tracy A. Propheter-Hinckley, Carey Clum, Timothy J. Jennings
  • MINICORE COOLING PASSAGE NETWORK HAVING TRIP STRIPS
    Publication number: 20210071580
    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: Application
    Filed: October 7, 2019
    Publication date: March 11, 2021
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • VARIABLE VANE ARRANGEMENT WITH VANE RECEPTACLE INSERT(S)
    Publication number: 20210071684
    Abstract: An assembly is provided for a variable vane arrangement of a turbine engine. A platform extends circumferentially about a centerline and radially relative to the centerline between a first platform side and a second platform side. The platform includes a plurality of variable vane receptacles arranged in an annular array about the axial centerline, which variable vane receptacles include a first variable vane receptacle. The first variable vane receptacle is configured with a recess, a bore and a shelf. The recess extends longitudinally along a variable vane pivot axis into the platform from the first platform side to the shelf. The bore extends longitudinally along the variable vane pivot axis into the platform from the shelf. An insert includes a sleeve and a plate. The sleeve lines at least a portion of the bore. The plate is located within the recess adjacent the shelf.
    Type: Application
    Filed: September 9, 2019
    Publication date: March 11, 2021
    Inventors: Robert R. Mayer, Peter F. Gero, Tracy A. Propheter-Hinckley