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).

  • Publication number: 20240037909
    Abstract: An example method for vane classification includes scanning, using a structured light scanner, a vane for a turbine engine to capture three-dimensional (3D) data about the vane. The method further includes generating a point cloud from the 3D data about the vane. The method further includes connecting, using a processing system, points of the point cloud to generate a mesh surface. The method further includes determining, using the processing system, an airflow for an airfoil of the vane based at least in part on the mesh surface. The method further includes constructing the turbine engine based at least in part on the airflow for the airfoil of the vane without reference to an adjacent airfoil of the vane.
    Type: Application
    Filed: July 29, 2022
    Publication date: February 1, 2024
    Inventors: Kun Tong, Tracy A. Propheter-Hinckley, Venumadhava Ponnala, Andres Diaz Alvarado
  • Publication number: 20240011400
    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines 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. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.
    Type: Application
    Filed: March 28, 2023
    Publication date: January 11, 2024
    Inventors: Scott A. Kovach, Tracy A. Propheter-Hinckley
  • Patent number: 11840930
    Abstract: A vane for a gas turbine engine, the vane including: an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side, the inner diameter platform has a suction side mate face and a pressure side mate face, wherein the suction side mate face and the pressure side mate face of the inner diameter platform have an axial feather seal slot and a radial seal slot, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the inner diameter platform and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the inner diameter platform, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot.
    Type: Grant
    Filed: May 17, 2019
    Date of Patent: December 12, 2023
    Assignee: RTX CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Craig R. McGarrah, Kyle J. Brevick, Egon Salimusaj
  • Publication number: 20230366317
    Abstract: A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.
    Type: Application
    Filed: June 22, 2023
    Publication date: November 16, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: RON I. PRIHAR, TRACY A. PROPHETER-HINCKLEY
  • Publication number: 20230366835
    Abstract: A method can comprise: scanning a tip of an airfoil of a bladed rotor, the tip including a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; comparing a coating parameter of the coating to a coating parameter threshold based on scanner data from the scanning; and determining whether the coating maintains sufficient coverage of the tip of the airfoil based on the comparing.
    Type: Application
    Filed: May 13, 2022
    Publication date: November 16, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ron I. PRIHAR, Elizabeth F. VINSON, Tracy A. PROPHETER-HINCKLEY, Garrett KERNOZICKY, Nigel D. SAWYERS-ABBOTT
  • Patent number: 11806953
    Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: August 24, 2022
    Date of Patent: November 7, 2023
    Assignee: RTX CORPORATION
    Inventors: Jonas S. Banhos, Tracy A. Propheter-Hinckley, Michael Parkin
  • Publication number: 20230314116
    Abstract: An inspection device is disclosed herein. In various embodiments, the inspection system device comprises: a support structure; a motor; a shaft operably coupled to the motor, the shaft extending from a first side of the support structure to a second side of the support structure, the shaft configured to couple to a bladed rotor; and a scanner moveably coupled to the support structure, the scanner configured to generate a three-dimensional model for the bladed rotor.
    Type: Application
    Filed: March 23, 2022
    Publication date: October 5, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: TRACY A. PROPHETER-HINCKLEY, DEREK J. MICHAELS, GARRETT KERNOZICKY
  • Patent number: 11773742
    Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
    Type: Grant
    Filed: March 2, 2020
    Date of Patent: October 3, 2023
    Assignee: RTX CORPORATION
    Inventors: Jonathan Ortiz, Raymond Surace, Renee J. Jurek, Tracy A. Propheter-Hinckley
  • Publication number: 20230306163
    Abstract: A method is disclosed herein. In various embodiments, the method comprises: coupling a sheath to an airfoil of an integrally bladed rotor, the sheath comprising a plurality of apertures disposed therein; and coupling a plurality of locators to the integrally bladed rotor, each locator in the plurality of locators disposed through a corresponding aperture in the plurality of apertures.
    Type: Application
    Filed: March 23, 2022
    Publication date: September 28, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: TRACY A. PROPHETER-HINCKLEY
  • Publication number: 20230304476
    Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: commanding, via the processor, a first scan of a bladed rotor; generating, via the processor, a three-dimensional model based on a first set of data received from the first scan; comparing, via the processor, the three-dimensional model to an acceptable three-dimensional model of the bladed rotor; determining, via the processor, areas of interest based on the comparison; commanding, via the processor, a second scan of the areas of interest of the bladed rotor; and generating a final three-dimensional model based on the first scan and the second scan.
    Type: Application
    Filed: March 23, 2022
    Publication date: September 28, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: TRACY A. PROPHETER-HINCKLEY, DEREK J. MICHAELS, LAWRENCE P. ROBERTS, RON I. PRIHAR
  • Publication number: 20230305156
    Abstract: An inspection system for a bladed rotor is disclosed herein. In various embodiments, the inspection system comprises: a support structure; a first scanner moveably coupled to the support structure; a second scanner moveably coupled to the support structure; a motor operably coupled to a shaft, the shaft rotatably coupled to the support structure, the shaft configured to be coupled to the bladed rotor; and a controller in electronic communication with the first scanner, the second scanner, and the motor, the controller configured to: command the first scanner to scan the bladed rotor; command the second scanner to scan the bladed rotor; and generate a point cloud for the bladed rotor based on scanning data received from the first scanner and the second scanner.
    Type: Application
    Filed: March 23, 2022
    Publication date: September 28, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: TRACY A. PROPHETER-HINCKLEY, DEREK J. MICHAELS, LAWRENCE P. ROBERTS
  • Patent number: 11753944
    Abstract: An airfoil section 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 airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: September 12, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Patent number: 11725517
    Abstract: A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.
    Type: Grant
    Filed: May 13, 2022
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Ron I. Prihar, Tracy A. Propheter-Hinckley
  • Patent number: 11707779
    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: June 29, 2021
    Date of Patent: July 25, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 11702941
    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines 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. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.
    Type: Grant
    Filed: August 6, 2019
    Date of Patent: July 18, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Scott A. Kovach, Tracy A. Propheter-Hinckley
  • Patent number: 11702987
    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: Grant
    Filed: September 21, 2021
    Date of Patent: July 18, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Scott A. Kovach, Tracy A. Propheter-Hinckley
  • Patent number: 11661853
    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: Grant
    Filed: September 23, 2021
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: San Quach, Tracy A. Propheter-Hinckley, Steven Bruce Gautschi
  • Patent number: 11661850
    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.
    Type: Grant
    Filed: August 6, 2019
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Publication number: 20230158758
    Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.
    Type: Application
    Filed: August 24, 2022
    Publication date: May 25, 2023
    Inventors: Jonas S. Banhos, Tracy A. Propheter-Hinckley, Michael Parkin
  • Publication number: 20230151737
    Abstract: An airfoil includes a platform and an airfoil section that extends from the platform. The airfoil defines leading and trailing ends and suction and pressure sides. The airfoil section has a transition region through which the airfoil section blends into the platform. The trailing end of the airfoil section has an axial cooling slot opening through the transition region and defines a circumferentially diverging ramp in the transition region.
    Type: Application
    Filed: November 17, 2022
    Publication date: May 18, 2023
    Inventors: Tracy A. Propheter-Hinckley, Dominic J. Mongillo, JR., Allan Nyairo Arisi