Patents Assigned to RAYTHEON TECHNOLOGY CORPORATION
  • Turbine over-speed brake for hybrid electric gas turbine engine
    Patent number: 11725580
    Abstract: An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.
    Type: Grant
    Filed: June 18, 2021
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Marc J. Muldoon, Michael D. Greenberg, Nancy Poisson, Martin Richard Amari
  • Deposition apparatus and methods
    Patent number: 11725269
    Abstract: A deposition apparatus (20) comprising: a chamber (22); a process gas source (62) coupled to the chamber; a vacuum pump (52) coupled to the chamber; at least two electron guns (26); one or more power supplies (30) coupled to the electron guns; a plurality of crucibles (32,33,34) positioned or positionable in an operative position within a field of view of at least one said electron gun; and a part holder (170) having at least one operative position for holding parts spaced above the crucibles by a standoff height H. The standoff height H is adjustable in a range including at least 22 inches.
    Type: Grant
    Filed: June 20, 2022
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Brian T. Hazel, Michael J. Maloney, James W. Neal, David A. Litton
  • Turbulence generator mixer for rotating detonation engine
    Patent number: 11725824
    Abstract: A combustor for a rotating detonation engine includes a radially outer wall extending along an axis (A); a radially inner wall extending along the axis (A), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a1) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a2) to the inlet, wherein the second passage axis is arranged at an angle (?) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.
    Type: Grant
    Filed: April 8, 2021
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Zhongtao Dai, Peter A T Cocks
  • Gas turbine engine having electric motor for applying power to a spool shaft and method for operating same
    Patent number: 11725578
    Abstract: A gas turbine engine includes a low-pressure spool, a high-pressure spool, and an electric motor. The low-pressure spool includes a low-pressure compressor in rotational communication with a low-pressure turbine and a fan via a first shaft. The high-pressure spool includes a high-pressure compressor in rotational communication with a high-pressure turbine via a second shaft. The electric motor is operably connected to the second shaft. The electric motor is configured to apply a rotational force to the second shaft.
    Type: Grant
    Filed: January 3, 2022
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Gary Collopy
  • Vane multiplet with common platform joining airfoils
    Patent number: 11725528
    Abstract: A vane multiplet includes a plurality of airfoils that each have a flared end, a common platform piece, a plurality of seal, and a plurality of retainers. The common platform has airfoil sockets that each define an airfoil opening that is circumscribed by a groove. The flared ends of the airfoils are seated in the airfoil sockets such that the grooves and the airfoils together form seal channels that have an open side. The seals are disposed in the seal channels. The retainers have airfoil-shaped profiles and are disposed in the airfoil sockets to bound the open sides of the seal channels and retain the seal in the seal channel.
    Type: Grant
    Filed: August 5, 2022
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Christian X. Campbell
  • Airfoil with wishbone fiber structure
    Patent number: 11725522
    Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.
    Type: Grant
    Filed: January 15, 2021
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jonas S. Banhos, Kathryn S. Read, Raymond Surace, Olivier H. Sudre
  • Method of servicing a gas turbine engine or components
    Patent number: 11725516
    Abstract: A method of servicing a gas turbine engine is disclosed. According to the method, a component including a titanium alloy is removed from the gas turbine engine after operating the gas turbine engine with the component in service. The removed component is subjected to heat treatment, and the heat-treated component is re-installed into the gas turbine engine or installed into a different gas turbine engine.
    Type: Grant
    Filed: October 18, 2019
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Sara Ann Beck, David Ulrich Furrer, Vasisht Venkatesh
  • Geared gas turbine engine with oil deaerator
    Patent number: 11725589
    Abstract: A gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction. The lubrication system includes a lubricant pump supplying a mixed air and oil to a deaerator inlet. The deaerator includes a separator that for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank. The separator includes a member having lubricant flow paths on both of two opposed sides. A method of designing a gas turbine engine is also disclosed.
    Type: Grant
    Filed: October 30, 2020
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: William G. Sheridan
  • Compressor flowpath
    Patent number: 11725670
    Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.
    Type: Grant
    Filed: August 22, 2022
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Lisa I. Brilliant, Becky E. Rose, Yuan Dong, Stanley J. Balamucki
  • Bore compartment seals for gas turbine engines
    Patent number: 11725531
    Abstract: Rotor systems including an engine shaft, a forward hub, a rear hub, a rotor disk arranged between the forward hub and the rear hub, and a seal tube configured to define a forward hub compartment and a rear hub compartment. The forward hub compartment is defined forward of the rotor disk and the rear hub compartment is defined aft of the rotor disk. The seal tube is connected at a forward end to at least one of the rotor disk and the engine shaft and at a rear end to at least one of the rear hub and the engine shaft and the seal tube includes at least one axial compliance element configured to enable axial extension and compression of the seal tube in an axial direction along the engine shaft.
    Type: Grant
    Filed: November 22, 2021
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Nicholas J. Lawliss, Paul Boules
  • Fluid transfer assembly for rotational equipment
    Patent number: 11725529
    Abstract: An inner structure is within an outer structure. A shield mount of a shield is attached to the outer structure. A sleeve of the shield extends from the shield mount through an aperture in the outer structure to a distal end of the shield. The sleeve is mated with the port at the distal end through a slip joint interface where a cylindrical sleeve surface of the sleeve contacts a cylindrical port surface of a port of the inner structure. The fluid transfer tube extends from an inner tube end through a bore of the shield and at least into the port to an outer tube end. An inner coupling is disposed at the inner tube end and mated with the inner structure through a cone seal interface. An outer coupling is disposed at the outer tube end and attached to the outer structure.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Andre H. Troughton
  • Seal runner with deflector and catcher for gas turbine engine
    Patent number: 11725694
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal runner, a seal configured to cooperate with the seal runner to seal the bearing compartment, and a catcher in contact with the seal runner to minimize deflection of the seal runner. A method is also disclosed.
    Type: Grant
    Filed: December 20, 2021
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Todd A. Davis, Dale C. Humphries
  • System and method for forming an ultra-high temperature composite structure
    Patent number: 11724967
    Abstract: A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a first polymeric precursor with a spinneret; forming a first plurality of nanofibers from the first polymeric precursor; depositing the first plurality of nanofibers with a collector; and applying a fluid, with a nozzle, onto the first plurality of nanofibers disposed on the collector. The fluid includes a second polymeric precursor.
    Type: Grant
    Filed: June 13, 2019
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Bart A. van Hassel, Sergei F. Burlatsky
  • Multi-direction hole for rail effusion
    Patent number: 11725816
    Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
    Type: Grant
    Filed: June 10, 2022
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Jon E. Sobanski, Steven D. Porter
  • Mounting a ceramic component to a non-ceramic component in a gas turbine engine
    Patent number: 11725823
    Abstract: A combustor with a centerline is provided that includes a support structure and a heat shield. The heat shield extends circumferentially about and axially along the centerline. The heat shield is configured from or otherwise includes ceramic material. The heat shield is mounted to the support structure by an interlocking joint connection. The interlocking joint connection includes a projection and a groove. The projection is configured with the support structure and includes a plurality of fingers arranged along and projecting into the groove. The groove is formed in the heat shield.
    Type: Grant
    Filed: January 3, 2022
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Stephen K. Kramer
  • Apparatuses and methods for removing a component
    Patent number: 11724372
    Abstract: An apparatus is provided for removing a component from a device, where the component includes a cylindrical portion and a shoulder adjacent the cylindrical portion. The apparatus includes a base, a puller and a shaft. The base includes a first mount, a second mount and a bridge extending between and connected to the first mount and the second mount. The first mount and the second mount are each configured to engage with the device. The puller includes a forked flange configured to abut against the shoulder of the component when the cylindrical portion of the component is within a channel of the forked flange. The shaft includes a threaded portion mated with a threaded aperture in the bridge. A distal end portion of the shaft is rotatably connected to the puller.
    Type: Grant
    Filed: February 7, 2022
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Kousha Emami
  • Leading edge hybrid cavities for airfoils of gas turbine engine
    Patent number: 11725521
    Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom are described. The core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.
    Type: Grant
    Filed: September 6, 2019
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dominic J. Mongillo, Jr.
  • Bluff-body piloted high-shear injector and method of using same
    Patent number: 11725818
    Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. A hood chamber is separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell. The bulkhead includes at least one opening extending between the hood chamber and the combustion chamber. A fuel injector extends through the at least one opening. The fuel injector includes a primary fuel passage including a primary fuel outlet located within the combustion chamber. The fuel injector further includes a secondary fuel passage including a plurality of secondary fuel outlets located within the hood chamber.
    Type: Grant
    Filed: December 6, 2019
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Timothy S. Snyder
  • Terahertz enhanced foreign object debris discrimination for optical particulate sensor
    Patent number: 11726035
    Abstract: A method of foreign object debris discrimination incudes illuminating particulates located within a sensing volume with a first electromagnetic radiation pulse emitted from a first source, and illuminating the particulates within the sensing volume with a second electromagnetic radiation pulse emitted from a second source, wherein the second electromagnetic radiation pulse has a second wavelength range within the terahertz (THz) regime. The first electromagnetic radiation returns and the second electromagnetic radiation returns are compared to determine a scattering ratio from the comparing step. The scattering ratio is then utilized to determine a resultant foreign object debris type of the solid objects.
    Type: Grant
    Filed: December 11, 2020
    Date of Patent: August 15, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: David L. Lincoln, Jose-Rodrigo Castillo-Garza
  • Switchover for redundant control systems
    Patent number: 11726859
    Abstract: A redundant control system includes a plurality of channels each including a processing system configured to execute a control application for a controlled system. The redundant control system also includes a switchover artificial intelligence control operable to evaluate a state of the channels of the redundant control system, monitor a plurality of input/output data and communication data of the channels, and apply a fault model to determine one or more component faults and system faults of the channels based on the state, the input/output data, and the communication data. The switchover artificial intelligence control is further operable to command a switchover of a control function from one of the channels having a lower health status to one of the channels having a higher health status based on the component faults and system faults of the channels.
    Type: Grant
    Filed: August 7, 2020
    Date of Patent: August 15, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Paul A. Adamski