Patents Examined by Arun Goyal
  • Patent number: 12012234
    Abstract: An electrodeless plasma thruster with closed-ring-shaped gas discharge chamber (1, 10) can include a gas discharge chamber (1, 10) closed-ring-shaped in fluid communication with a propellant storage system (10, 70). An antenna (3, 30) can be positioned on the exterior of the gas discharge tube (1, 10). A guide tube (2, 20) can be coupled with the gas discharge chamber (1, 10) at a first end and have a second open end. A magnetic system (7, 50) can be positioned on the second end of the guide tube (2, 20). The magnetic system (7, 50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11, 80) and a control module.
    Type: Grant
    Filed: September 7, 2021
    Date of Patent: June 18, 2024
    Assignee: Khalifa University of Science and Technology
    Inventors: Andrei Ivanovich Shumeiko, Firas Salah Jarrar, Sean Shan Min Swei
  • Patent number: 12006923
    Abstract: An intake system for an atmosphere-breathing electric thruster is disclosed, comprising an inlet for inflow of atmosphere particles, an outlet for coupling to the thruster for fueling collected atmosphere particles to the thruster, a collector arranged between the inlet and the outlet comprising multiple channels for allowing inflowing atmosphere particles to pass through the channels towards the outlet, the channels defining an inlet area and a length, wherein a position of at least part of the channels is adjustable to alter at least one of the inlet area and the length.
    Type: Grant
    Filed: February 22, 2021
    Date of Patent: June 11, 2024
    Assignee: VKI—von Karman Institute for Fluid Dynamics
    Inventors: Damien Le Quang, Zuheyr Alsalihi, Pietro Parodi
  • Patent number: 12006922
    Abstract: Precision flow restrictors and techniques for manufacturing the same for ion thruster manifolds are disclosed. Flow restricting features are moved out of the manifold base and into separate flow restrictors, allowing a wider range of manufacturing techniques and materials to be applied. Quality control can be performed at the level of the flow restrictors as subcomponents, ensuring that only good parts with ideal flow characteristics make it into the final assembly and improving the yield rate of the final manifold assembly.
    Type: Grant
    Filed: February 24, 2020
    Date of Patent: June 11, 2024
    Assignee: United States of America as Represented by the Administrator of National Aeronautics and Space Administration
    Inventors: Timothy G. Gray, Gabriel F. Benavides
  • Patent number: 12006069
    Abstract: A method and apparatus uses a VLF transmitter, a VLF receiver, and/or a low earth orbit satellite including a rocket engine. A VLF wave transmitted into space is converted to an ambient wave. The ambient wave acts as a signal wave for a whistler traveling wave parametric amplifier. Rocket exhaust is generated in atmospheric plasma. The rocket exhaust includes kinetic energy acting as a Lower Hybrid wave source. The Lower Hybrid wave source produces a Lower Hybrid wave, which acts as a pump wave for the parametric amplifier. Nonlinear mixing of the signal wave and the pump wave in the atmospheric plasma simultaneously parametrically amplifies the ambient wave and generates an idler wave and a parametrically amplified wave. The parametrically amplified wave (1) reduces the density of energetic protons or killer electrons in the Van Allen radiation belt, and (2) improves communications between the VLF transmitter and VLF receiver.
    Type: Grant
    Filed: December 10, 2021
    Date of Patent: June 11, 2024
    Assignee: The Government of the United States of America, as represented by the Secretary of the Navy
    Inventor: Paul A. Bernhardt
  • Patent number: 12000336
    Abstract: A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.
    Type: Grant
    Filed: June 29, 2022
    Date of Patent: June 4, 2024
    Assignee: Jetoptera, Inc.
    Inventor: Andrei Evulet
  • Patent number: 11993402
    Abstract: An ion propulsion device including emission modules in an emission plane, each module having an insulating support, an emission electrode on the support, and a conductive liquid with a microfluidic channel depositing conductive liquid on the electrode; an extraction electrode common to the emission modules and facing the modules; and a control unit, in which each module is configured to emit an ion beam when an electric field is applied to the liquid; each control unit controls an ion emission current emitted by applying a potential difference between each emission electrode and the extraction electrode; the emission electrodes are spaced apart by a linear distance that is greater than a distance between two adjacent emission electrodes separated by an empty space; and a length of the insulating support between the electrodes is greater than a propagation distance of an electric leakage current by charge jumping along the support between the electrodes.
    Type: Grant
    Filed: September 22, 2020
    Date of Patent: May 28, 2024
    Assignees: CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, CENTRE NATIONAL D'ETUDES SPATIALES, UNIVERSITE PARIS-SACLAY
    Inventors: Jacques Gierak, Claude Boniface, Mathieu Lepesant
  • Patent number: 11994295
    Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.
    Type: Grant
    Filed: February 18, 2022
    Date of Patent: May 28, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Pradeep Naik, Shai Birmaher, Kwanwoo Kim, Saket Singh, Perumallu Vukanti, Karthikeyan Sampath, Steven C. Vise, Nicholas R. Overman, Michael A. Benjamin
  • Patent number: 11987375
    Abstract: Methods and systems for operating an aircraft having two or more engines are described. The method comprises receiving an engine availability confirmation when a set of engine parameters meet engine operating conditions for an asymmetric operating regime, receiving an aircraft availability confirmation when a set of aircraft parameters meet aircraft operating conditions for the asymmetric operating regime, outputting an availability message to a cockpit of the aircraft in response to receiving the engine availability confirmation and the aircraft availability confirmation, receiving a pilot-initiated request to operate the engine in the asymmetric operating regime, and commanding the engines to operate in the asymmetric operating regime in response to the pilot-initiated request.
    Type: Grant
    Filed: October 16, 2019
    Date of Patent: May 21, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Patrick Manoukian, Keith Morgan
  • Patent number: 11988145
    Abstract: According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; and a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of the first component.
    Type: Grant
    Filed: January 7, 2019
    Date of Patent: May 21, 2024
    Assignee: RTX CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11982237
    Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.
    Type: Grant
    Filed: November 9, 2022
    Date of Patent: May 14, 2024
    Assignee: Collins Engine Nozzles, Inc.
    Inventors: Jason Ryon, Lev Alexander Prociw
  • Patent number: 11976588
    Abstract: Gas turbine power plants augmented with an air injection system for hot air injection to augment power and are used to drive sensitive cogeneration processes are fitted with compressed air storage capability to more smoothly ramp on air injection in the event of sudden and unexpected interruption of the air injection system. Utilizing stored hot air injection prior to starting an air injection system significantly reduces the start-up time of the air injection system.
    Type: Grant
    Filed: January 28, 2019
    Date of Patent: May 7, 2024
    Assignee: Powerphase International, LLC
    Inventors: Robert J. Kraft, Plazi Ricklin
  • Patent number: 11976642
    Abstract: Some embodiments of the invention include a thruster system comprising a thruster and a pulsing power supply. The thruster may include a gas inlet port; a plasma jet outlet; and a first electrode. In some embodiments, the pulsing power supply may provide an electrical potential to the first electrode with a pulse repetition frequency greater than 10 kHz, a voltage greater than 5 kilovolts. In some embodiments, the pressure downstream from the thruster can be less than 10 Torr. In some embodiments, when a plasma is produced within the thruster by energizing a gas flowing into the thruster through the gas inlet port, the plasma is expelled from the thruster through the plasma jet outlet.
    Type: Grant
    Filed: December 22, 2022
    Date of Patent: May 7, 2024
    Assignee: EHT Ventures LLC
    Inventors: Timothy M. Ziemba, James R. Prager, John G. Carscadden, Kenneth E. Miller, Ilia Slobodov, Julian F. Picard, Akel Hashim
  • Patent number: 11971173
    Abstract: A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores. An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores.
    Type: Grant
    Filed: July 23, 2021
    Date of Patent: April 30, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eduardo Hawie, Nigel Davenport
  • Patent number: 11959643
    Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
    Type: Grant
    Filed: June 7, 2021
    Date of Patent: April 16, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Karthikeyan Sampath, Pradeep Naik, Veeraraju Vanapalli, Perumallu Vukanti, Shai Birmaher, Daniel J. Kirtley, Deepak Ghiya, Rimple Rakeshkumar Rangrej, Saket Singh, Ravindra Shankar Ganiger, Hiranya Kumar Nath, Michael Anthony Benjamin, Rajendra Mahadeorao Wankhade
  • Patent number: 11961666
    Abstract: The present invention discloses an electric field propulsion system for spacecraft. The system includes a capacitor stack comprising an array of supercapacitors. Solid-state electronic circuits generate modulated currents and electric fields in pulse coils. The pulse coils direct the electric fields onto separated electric charges stored in the capacitor stack. The resulting unidirectional Lorentz Forces thereby generate thrust without reaction mass. Reaction momentum is carried away by Poynting Vector fields in conformity with the currently understood principles of electrodynamics. The design is scalable down to micro-chip sized thrusters.
    Type: Grant
    Filed: August 6, 2020
    Date of Patent: April 16, 2024
    Inventor: James W. Purvis
  • Patent number: 11952903
    Abstract: A microturbine comprising a turbine. a compressor, and an electric generator operating on a single shaft. The microturbine is designed segmenting the assembly into three subassemblies: a micro turbine engine subassembly, a turbine air sourcing housing subassembly, and a compressor air supply and electronics subassembly. The configuration enables efficient assembly, maintenance and repairs, as the operational components can be diagnosed at a high level and the subassembly can be exchanged quickly to optimize uptime. The micro turbine engine subassembly includes an integrated ceramic compressor and turbine assembly and a generator installed in a single unit that is slideably inserted within an interior of the turbine air sourcing housing subassembly. The compressor air supply and electronics subassembly is assembled to a respective end of the turbine air sourcing housing subassembly. The microturbine creates compressed air, heated air, and electrical power.
    Type: Grant
    Filed: June 22, 2020
    Date of Patent: April 9, 2024
    Assignee: GALILEO TECHNOLOGIES CORP.
    Inventor: Osvaldo Del Campo
  • Patent number: 11946412
    Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.
    Type: Grant
    Filed: September 13, 2019
    Date of Patent: April 2, 2024
    Assignee: RTX CORPORATION
    Inventors: Gabriel L. Suciu, James D. Hill
  • Patent number: 11940151
    Abstract: A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.
    Type: Grant
    Filed: March 15, 2022
    Date of Patent: March 26, 2024
    Assignee: General Electric Company
    Inventors: Michael T. Bucaro, Clayton S. Cooper
  • Patent number: 11939966
    Abstract: The present technology is directed to plasma systems and associated methods, including propulsion systems for flight vehicles. A representative system includes a plurality of coils. The coils include a first coil positioned along a force axis, a second coil positioned along the force axis and spaced apart from the first coil, and a third coil that is magnetically shielded. A controller is operatively coupled to the coils and is configured to (a) increase energy to the first coil to generate a magnetic field in a portion of the plasma adjacent to the first coil, (b) decrease energy to the first coil and increase energy to the second coil to translate the resulting superposed magnetic field through the plasma to a position adjacent the second coil, and (c) transfer energy from the second coil to the third coil and decrease energy to the second coil to reduce the magnetic field in the plasma.
    Type: Grant
    Filed: December 9, 2020
    Date of Patent: March 26, 2024
    Assignee: ELECTRIC SKY HOLDINGS, INC.
    Inventor: Jeffrey Greason
  • Patent number: 11933182
    Abstract: There is described a multi-channel, multi-range transducer for measuring a parameter, the transducer comprising N channels and M sensing elements, the M sensing elements centered on distinct calibration points of distinct measuring ranges, the M sensing elements distributed across the N channels of the transducer, wherein sensing elements having adjacent measuring ranges are provided in different ones of the N channels.
    Type: Grant
    Filed: March 24, 2020
    Date of Patent: March 19, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Paul Smith, Piotr Szczesnowicz