Patents Assigned to Raytheon Technologies Corporation
  • Vane arc segment with radially projecting flanges
    Patent number: 11668199
    Abstract: A vane arc segment includes an airfoil fairing that has first and second platforms and an airfoil section. The platforms have first and second openings that open into the airfoil section. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side. The first platform has a first flange that projects radially from the non-gaspath side aft of the first opening and a second flange that projects radially from the non-gaspath side forward of the first opening. The first and second flanges are exclusive flanges on the first platform. The second platform has a third flange that projects radially from the non-gaspath side aft of the second opening.
    Type: Grant
    Filed: March 5, 2021
    Date of Patent: June 6, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Jon E. Sobanski, Howard J. Liles, Chang Gao
  • Fiber-reinforced self-healing environmental barrier coating
    Patent number: 11668198
    Abstract: An environmental barrier coating system for a turbine component, including an environmental barrier layer applied to a turbine component substrate containing silicon; the environmental barrier layer comprising an oxide matrix surrounding a fiber-reinforcement structure and a self-healing phase interspersed throughout the oxide matrix; wherein the fiber-reinforcement structure comprises at least one first fiber bundle oriented along a load bearing stress direction of said turbine component substrate; wherein the fiber-reinforcement structure comprises at least one second fiber bundle oriented orthogonal to the at least one first fiber bundle orientation; wherein the fiber-reinforcement structure comprises at least one third fiber woven between the at least one first fiber bundle and the at least one second fiber bundle.
    Type: Grant
    Filed: August 3, 2018
    Date of Patent: June 6, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Richard Wesley Jackson, John E. Holowczak, Xia Tang, James T. Beals
  • Airfoil core inlets in a rotating vane
    Patent number: 11668202
    Abstract: A component for a gas turbine engine includes an airfoil, including therein a first cavity and a second cavity, and an outer spindle extending from the airfoil, the outer spindle including a first channel in fluid communication with the first cavity and a second channel in fluid communication with the second cavity.
    Type: Grant
    Filed: August 6, 2018
    Date of Patent: June 6, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Corey D. Anderson
  • Method and apparatus for auto-aligning of a process gas jet nozzle and laser machining beam
    Patent number: 11660703
    Abstract: An adjustment collar for a laser machine tool includes a first actuator between an outer housing and an inner collar, the first actuator operable to move the inner collar with respect to the outer housing in the X-axis and a second actuator between the outer housing and the inner collar, the second actuator operable to move the inner collar with respect to the outer housing in the Y-axis.
    Type: Grant
    Filed: March 23, 2021
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Anthony Pizzola
  • Multi-environmental barrier coating, processes for coating articles, and their coated articles
    Patent number: 11661380
    Abstract: A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a metal silicide phase, a crystalline ceramic phase and an amorphous ceramic phase, wherein the metal silicide phase has an aspect ratio greater than 1:1 but less than 50:1.
    Type: Grant
    Filed: August 6, 2021
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Richard Wesley Jackson, James T. Beals, Xia Tang, Xuan Liu, David A. Litton, Brian T. Hazel
  • Turbine blade trailing edge cooling feed
    Patent number: 11661852
    Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
    Type: Grant
    Filed: February 7, 2020
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Nicholas M. LoRicco, Parth Jariwala, Alex J. Schneider, Bret M. Teller, Matthew S. Gleiner, Jeffrey T. Morton
  • Airfoil tip pocket with augmentation features
    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
  • Propulsion system arrangement for turbofan gas turbine engine
    Patent number: 11661906
    Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.
    Type: Grant
    Filed: July 9, 2021
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Christopher A. Eckett, Gabriel L. Suciu
  • Mounting device and method for mounting components
    Patent number: 11661967
    Abstract: A mounting device includes a first mount portion and a second mount portion. The first mount portion is in communication with a first pin extending along a first axis. The second mount portion is in communication with a pair of opposing second pins extending along a second axis different than the first axis. The second pins are in rotational communication with and extend outward from the first pin. The first and second mount portions are configured to translate along the first and second axes and rotate about the first and second axes with respect to one another.
    Type: Grant
    Filed: April 17, 2019
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Michael R. Thomas
  • Gas turbine engine component
    Patent number: 11661865
    Abstract: A method of assembling a blade outer air seal assembly includes engaging a first blade outer air seal with a first attachment surface on a first attachment body. The first blade outer air seal includes a first attachment body passage for accepting the first attachment body. A second blade outer air seal is engaged with a second attachment surface on the first attachment body. The second blade outer air seal includes a second attachment body passage for accepting the first attachment body. Rotation is prevented of the first attachment body relative to the first blade outer air seal with a first post engaging the first blade outer air seal. Rotation is prevented of the first attachment body relative to the second blade outer air seal with a second post engaging the second blade outer air seal.
    Type: Grant
    Filed: July 18, 2022
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Thomas E. Clark, Ken F. Blaney
  • Radially outward orbital welding technique as a joining method used for inner tube to fitting connections in double wall tube configurations
    Patent number: 11660711
    Abstract: A process of welding fittings to ends of a double wall pipe comprising forming a first welded joint between an inner pipe and an inner receiver of a first fitting; forming a second welded joint between an outer pipe and an outer receiver of the first fitting; forming a third welded joint between the outer pipe and an outer receiver of a second fitting; and forming a fourth welded joint between the inner pipe and an inner receiver of the second fitting.
    Type: Grant
    Filed: June 6, 2019
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Pawel Kaniowski, Piotr Kaczor, Robert Wozniak, Wangen Lin, Christopher A. Sanchez
  • Geared turbine engine with relatively lightweight propulsor module
    Patent number: 11661894
    Abstract: An example gas turbine engine includes a propulsor assembly consisting of a fan module and a fan drive turbine module, an epicyclic gear train, a high spool and a low spool. A weight of the propulsor assembly is less than 40% of a total weight of a gas turbine engine. The high spool includes an outer shaft, a high pressure turbine and a high pressure compressor. The low spool includes an inner shaft, a low pressure turbine and a low pressure compressor. The inner shaft drives the propulsor through the gear train to drive the propulsor. A weight of the propulsor is greater than a weight of the low pressure turbine.
    Type: Grant
    Filed: December 20, 2021
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu
  • Hydrogen powered geared turbo fan engine with an off-set reduced core
    Patent number: 11661889
    Abstract: Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.
    Type: Grant
    Filed: January 21, 2022
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Marc J. Muldoon, Joseph B. Staubach
  • Alkaline manganese redox flow battery with inhibitor
    Patent number: 11664518
    Abstract: A redox flow battery includes a redox flow cell and a supply and storage system external of the redox flow cell. The supply and storage system includes first and second electrolytes for circulation through the redox flow cell. The first electrolyte is a liquid electrolyte having electrochemically active manganese species with multiple, reversible oxidation states in the redox flow cell. The electrochemically active manganese species may undergo reactions that cause precipitation of manganese oxide solids. The first electrolyte includes an inhibitor that limits the self-discharge reactions. The inhibitor includes an oxoanion compound.
    Type: Grant
    Filed: May 21, 2021
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy Davenport, James D. Saraidaridis, Robert Mason Darling
  • Low density hybrid knife seal
    Patent number: 11661855
    Abstract: A hybrid abradable seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending radially from the external surface; an abradable material disposed within the casing; the abradable material and the casing being coupled together and configured to resist a deflection responsive to engine gas loads.
    Type: Grant
    Filed: October 25, 2021
    Date of Patent: May 30, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: John Harner, Kerry Lynn Davis, David J. Mathiau
  • Airfoil with convex sides and multi-piece baffle
    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
  • Thermal Barrier Coating
    Publication number: 20230160070
    Abstract: A coated substrate has a substrate and a coating system having one or more ceramic layers. At least a first layer of one of the one or more ceramic layers is a columnar layer having as-deposited columns and intercolumn gaps. The intercolumn gaps have a mean width at least one of: at least 4.0 micrometers; and at least 1.5% of a thickness of said first layer.
    Type: Application
    Filed: April 27, 2021
    Publication date: May 25, 2023
    Applicant: Raytheon Technologies Corporation
    Inventors: Brian T. Hazel, Xuan Liu, Kaylan M. Wessels, Elisa M. Zaleski, Kimberly M. Adams, Richard W. Jackson
  • UNIT CELL RESONATOR NETWORKS FOR GAS TURBINE COMBUSTOR TONE DAMPING
    Publication number: 20230160343
    Abstract: A noise attenuation panel for a structure within a propulsion system includes a first plurality of unit cells; and a second plurality of unit cells, the second plurality of unit cells merged within the first plurality of unit cells, the first plurality of unit cells including a first periodic structure having a first unit cell, a second unit cell, a third unit cell and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells.
    Type: Application
    Filed: November 24, 2021
    Publication date: May 25, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Julian Winkler, Kenji Homma, Craig Aaron Reimann, Jeffrey Michael Mendoza
  • Aircraft Heat Exchanger Panel Attachment
    Publication number: 20230160641
    Abstract: A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has at least one plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has a first face to which the plurality of plates are mounted along their respective proximal edges. An inlet plenum has at least one inlet port and at least one outlet port. An outlet plenum has at least one outlet port and at least one inlet port.
    Type: Application
    Filed: January 9, 2023
    Publication date: May 25, 2023
    Applicant: Raytheon Technologies Corporation
    Inventors: Patrick M. Hart, William P. Stillman, Russell J. Bergman
  • Aircraft Heat Exchangers
    Publication number: 20230160342
    Abstract: A turbine engine heat exchanger has: a manifold having a first face and a second face opposite the first face; a plurality of first plates along the first face, each first plate having an interior passageway; and a plurality of second plates along the second face, each second plate having an interior passageway. A first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates.
    Type: Application
    Filed: January 23, 2023
    Publication date: May 25, 2023
    Applicant: Raytheon Technologies Corporation
    Inventors: James F. Wiedenhoefer, Russell J. Bergman, William P. Stillman, Patrick M. Hart