Patents Examined by William Breazeal
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Patent number: 9958163Abstract: A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss. In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).Type: GrantFiled: October 10, 2014Date of Patent: May 1, 2018Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Shohei Numata, Osami Yokota, Tetsuma Tatsumi, Akinori Hayashi
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Patent number: 9951658Abstract: A system includes an oxidant compressor and a gas turbine engine. The gas turbine engine includes a combustor section having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine. The exhaust gas compressor is configured to compress and route an exhaust flow to the turbine combustor and the oxidant compressor is configured to compress and route an oxidant flow to the turbine combustor. The gas turbine engine also includes an inlet oxidant heating system configured to route at least one of a first portion of the combustion products, or a second portion of the exhaust flow, or any combination thereof, to an inlet of the oxidant compressor.Type: GrantFiled: June 25, 2014Date of Patent: April 24, 2018Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Vahid Vaezi, Franklin F. Mittricker, Richard A. Huntington
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Patent number: 9951656Abstract: The invention relates to a method for operating a gas turbine system, wherein the gas turbine system includes a compressor, a combustor, a heat recovery steam generator, a scrubber, a direct contact cooler. The method includes introducing the scrubbing fluid discharged from the scrubber into the direct contact cooler, contacting the scrubbing fluid in the direct contact cooler with the exhaust gas discharged from the heat recovery steam generator in order to remove a portion of nitrogen oxide therefrom; feeding the exhaust gas discharged from the direct contact cooler into the compressor. With the technical solution of the present invention, nitrogen oxide in the exhaust gas is reduced to a certain extent by means of used scrubbing fluid from the scrubber. This solution may improve the efficiency in reduction of nitrogen oxide with a simple and feasible manner.Type: GrantFiled: September 23, 2014Date of Patent: April 24, 2018Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Wuyin Wang, Vasileios Stefanis, Julie Clavier, Mirco Colombo, Felix Guethe
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Patent number: 9945265Abstract: A power generation system having a gas turbine, a fuel cell, an exhaust air circulation line, an exhaust fuel gas supply line, a turbine, an exhaust heat recovery boiler, and at least one exhaust air heat exchanger. The turbine is equipped with a high-pressure turbine, a medium-pressure turbine, and a low-pressure turbine. The exhaust heat recovery boiler is equipped with a high-pressure steam circulation mechanism, a medium-pressure steam circulation mechanism, and a low-pressure steam circulation mechanism. The exhaust air heat exchanger exchanges heat between the steam exchanging heat with the exhaust gas in the high-pressure steam circulation mechanism or the medium-pressure steam circulation mechanism and flowing toward the turbine and the exhaust gas flowing through the exhaust air circulation line, thereby increasing the temperature of the steam and decreasing the temperature of the exhaust gas.Type: GrantFiled: November 5, 2013Date of Patent: April 17, 2018Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Yukimasa Nakamoto, Kazunori Fujita
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Patent number: 9926809Abstract: A method for discharging exhaust gas from a gas turbine wherein a number of sectors, position, and angle at the center of at least one sector of a peripheral opening capable of forming an area for reingestion of a primary flow into an engine bay are determined by correlation of interactions between secondary cooling flows and the primary flow, from following behavior parameters: air gyration and speed at an inlet of a pipe, geometry of an exhaust stream, routing of the secondary cooling flow for cooling the engine bay, and a geometry and position of inlets of the secondary flows. The peripheral opening is then closed over the identified at least one angular sector. The method prevents backflow of hot primary air into the peripheral opening formed between a pipe and an ejector of the exhaust stream of a gas turbine.Type: GrantFiled: February 1, 2013Date of Patent: March 27, 2018Assignee: TURBOMECAInventors: Fabian Ammon, Alexandre Brisson, Guy Crabe, Jacques Demolis, Laurent Houssaye, Julien Munoz
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Patent number: 9908641Abstract: A satellite propulsion system comprises: at least one tank containing a propulsion reagent, and at least one tank containing a pressurizing gas that pressurizes the propulsion reagent, at least one transport means for transporting the pressurizing gas from the pressurizing gas tank to the propulsion reagent tank, the transport means comprising at least one opening allowing a continuous leak-off of pressurizing gas, and at least one device intended, after the satellite has entered operational orbit, to isolate a zone comprising the opening from the rest of the propulsion system.Type: GrantFiled: July 10, 2015Date of Patent: March 6, 2018Assignee: THALESInventor: Laurent Fontaine
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Patent number: 9909495Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.Type: GrantFiled: January 20, 2015Date of Patent: March 6, 2018Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Wesley K. Lord, Jesse M. Chandler, Michael Winter, Michael E. McCune, William G. Sheridan
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Patent number: 9909574Abstract: A method for operating self-pressurizing propellants in space thruster chambers and nozzles heated by resistive, radiative or nuclear methods at temperatures hundreds of degrees above the decomposition temperature. The method is defined by reducing the chamber volume Vc and increasing the nozzle throat area A* such that a propellant vapor with sonic velocity a* experiences a high temperature residence time that is less than 10 milliseconds. In other aspects of the invention propellant vapor is formed from a self-pressurizing propellant and the residence time is such that the propellant vapor does not decompose nor does the propellant vapor polymerize to a solid.Type: GrantFiled: May 2, 2016Date of Patent: March 6, 2018Assignee: CU Aerospace, LLCInventors: Neil J. Heimanowski, Curtis A. Woodruff, Rodney L. Burton, David L. Carroll
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Patent number: 9897079Abstract: The invention is a Hall thruster that does not have any discharge channel, and magnetic pole piece. The Hall thruster utilizes permanent magnets to produce magnetic field with strong radial component in front of an annular anode, and expands propellant directly into vacuum through the anode acting also as a gas distributor. The invention reduces mass and complexity of conventional Hall thrusters, and offers a radical solution to discharge channel and magnetic pole piece erosion problem.Type: GrantFiled: December 22, 2016Date of Patent: February 20, 2018Inventor: Burak Karadag
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Patent number: 9874202Abstract: A Hall thruster apparatus having walls constructed from a conductive material, such as graphite, and having magnetic shielding of the walls from the ionized plasma has been demonstrated to operate with nearly the same efficiency as a conventional nonmagnetically shielded design using insulators as wall components. The new design is believed to provide the potential of higher power and uniform operation over the operating life of a thruster device.Type: GrantFiled: July 25, 2016Date of Patent: January 23, 2018Assignee: CALIFORNIA INSTITUTE OF TECHNOLOGYInventors: Dan Michael Goebel, Richard Robert Hofer, Ioannis G. Mikellides
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Patent number: 9874111Abstract: A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint.Type: GrantFiled: September 5, 2014Date of Patent: January 23, 2018Assignee: United Technologies CorporationInventors: Michael S. Stevens, Ken F. Blaney
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Patent number: 9863364Abstract: NMSET and related device uses and improvements to the forces generated. Laminar flow control systems benefit from NMSET and related devices as they simplify installation and are easier to retrofit on existing aircraft. Necessary temperature gradients can me generated by using a heated material with the sides at different energy accommodation coefficients. Surface geometries can be used to increase the force generated. Photovoltaic film can be embedded into the membrane, providing a source of energy that can offset the power required for desired thrust. Intake scoops improve the air flow through the micro thrusters and surface geometries, and airflow diffusers increase air flow interaction with the hotter surface resulting in higher thrust outputs.Type: GrantFiled: June 14, 2013Date of Patent: January 9, 2018Assignee: GAME CHANGERS, LLCInventors: Piotr A. Garbuz, Jason D. Sanchez
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Patent number: 9862498Abstract: A high-speed propulsion system for a high-speed vehicle includes an air intake duct, a compression section, a combustion section, and an expansion section. A gas dynamic laser generator is disposed proximate the expansion section and generates a source of laser light. A laser transmission mechanism receives the laser light and transmits the laser light from the gas dynamic laser generator to the combustion section and to presents the laser light into the air/fuel mixture of the flowpath which promotes mixing, combustion, and flame stability.Type: GrantFiled: July 8, 2014Date of Patent: January 9, 2018Inventors: Byron Wells, Matthias Ihme
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Patent number: 9856862Abstract: A propulsion system for spacecraft is based on an electric engine that expels propellant to achieve thrust. The propellant is first ionized to generate a plasma. Plasma particles are selectively accelerated via a pulsed laser that accelerates predominantly the electrons in the plasma. The electrons are expelled first, forming a space charge that acts as a virtual cathode to accelerate the positive ions. Interactions between the laser beam and plasma electrons are predominantly through the ponderomotive force.Type: GrantFiled: March 13, 2014Date of Patent: January 2, 2018Inventor: Wesley Gordon Faler
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Patent number: 9854660Abstract: An ion accelerator includes: an inner magnet having a channel extending through it in an axial direction; an outer magnet extending around the inner magnet, the magnets having like polarities so as to produce a magnetic field having two locations of zero magnetic field strength. The locations are spaced apart in the axial direction; and an anode and a cathode are arranged to generate an electrical potential difference between the locations.Type: GrantFiled: June 18, 2013Date of Patent: December 26, 2017Assignees: ASTRIUM SAS, ASTRIUM LIMITEDInventor: Aaron Kombai Knoll
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Patent number: 9796487Abstract: A fuel-free spacecraft propelling system having an open-ended outer cylinder of a propelling device and an atomic oxygen collecting device is disclosed. The latter is arranged at the forwardly-propelled front end of the outer cylinder and is hermetically connected with an RF generating device and an ion cyclotron wave heating device through a magnetic confinement device. A spiral wave discharge oxygen plasma inlet and a spiral wave discharge oxygen plasma outlet in the ion cyclotron wave heating device are respectively provided with another magnetic confinement device. The propulsion of the invention does not need to carry the propellant, which greatly reduces the launch costs, and enables a spacecraft to advantageously have an increased orbit life over existing spacecraft systems.Type: GrantFiled: May 7, 2013Date of Patent: October 24, 2017Assignee: Beijing Institute of Spacecraft Environment EngineeringInventors: Zhong Yi, Chao Zhang, Lifei Meng, Haifu Jiang, Yenan Liu, Qi Xiao, Lixiang Jiang, Zhaoji Yu
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Patent number: 9771865Abstract: An inlet bleed heat (IBH) system manifold for a compressor inlet housing is provided. The manifold includes: a plurality of feed pipes for delivering a compressor discharge air, each feed pipe extending across a duct of the compressor inlet housing. Each feed pipe includes: an elongated inner feed pipe for delivering the compressor discharge air, the inner feed pipe including a plurality of orifices along at least a portion of a length of the inner feed pipe, each orifice extending through a wall of the inner feed pipe allowing the compressor discharge air to exit the inner feed pipe; and a noise attenuating material disposed about the inner feed pipe and the plurality of orifices, the noise attenuating material configured to attenuate noise created by the compressor discharge air exiting the plurality of orifices.Type: GrantFiled: October 28, 2014Date of Patent: September 26, 2017Assignee: General Electric CompanyInventors: Laxmikant Merchant, Richard Lynn Loud, Valery Ivanovich Ponyavin, Dinesh Venugopal Setty, Hua Zhang
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Patent number: 9726114Abstract: Techniques, devices and systems are disclosed for implementing acoustically triggered propulsion of nano- and micro-scale structures. In one aspect, an ultrasound responsive propulsion device includes a tube that includes one or more layers including an inner layer having an electrostatic surface, and an ultrasound-responsive substance coupled to the inner layer and configured to form gaseous bubbles in a fluid in response to an ultrasound pulse, in which the bubbles exit the tube to propel the tube to move in the fluid.Type: GrantFiled: February 19, 2013Date of Patent: August 8, 2017Assignee: THE REGENTS OF THE UNIVERSITY OF CALIFORNIAInventors: Joseph Wang, Sadik C. Esener, Daniel Kagan, Michael Benchimol, Jonathan Claussen
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Patent number: 9708978Abstract: A heat engine for use in conjunction with a power generating plant, including a turbine section having a number of turbines, a heat exchanger section having a number of modules through which the expanded working fluid of the power generating plant and other sources of heat are circulated, a laminar flow inducing section, and a tower section for providing a pressure differential across the turbines of the turbine section. In use, the heat engine provides the dual function of: heating air to generate an updraft such that air forces its way into the turbine sections to drive the turbines and generate additional electricity; and using incoming colder air to condense the expanded working fluid and cool other sources of heat.Type: GrantFiled: March 12, 2012Date of Patent: July 18, 2017Inventor: Murray R. K. Johnson
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Patent number: 9664391Abstract: An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.Type: GrantFiled: November 27, 2013Date of Patent: May 30, 2017Assignees: KAWASAKI JUKOGYO KABUSHIKI KAISHA, JAPAN AEROSPACE EXPLORATION AGENCYInventors: Masayoshi Kobayashi, Takeo Oda, Ryusuke Matsuyama, Atsushi Horikawa, Hitoshi Fujiwara