Combustion Products Used As Motive Fluid Patents (Class 60/39.01)
  • Patent number: 10082080
    Abstract: A forward fan rotor is disclosed with a hub of axis of rotation (X) and a cone mounted on the hub of the fan. The cone comprises an air bleed orifice which opens into an air duct of which a forward end portion passes through the fan rotor, said forward end portion comprising mechanical air entrainment means. The air bleed orifice has an annular shape and in that the cone is divided by said orifice into a front vertex portion and a rear frustoconical portion. A turbomachine forward axial spool equipped with such a fan rotor is also disclosed.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: September 25, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christian Vessot, Matthieu Leyko
  • Patent number: 9038361
    Abstract: The present invention relates to a combustion controller for controlling the combustion of a flow of combustible and/or combusting fluid. The combustion controller comprises an inlet and an outlet which defines a flow path between them. A magnetic-field generator is arranged to generate a magnetic field across the flow path such that in use the fluid flows in the flow path through the magnetic field. As the fluid flows through the magnetic field an electric current is induced in the fluid. This results in energy being supplied to the fluid. This energy can assist is reignition. If the magnetic field is an alternating magnetic field then this induces an alternating current in the fluid. The frequency of this current can be controlled such that certain chemical reactions are either promoted or inhibited.
    Type: Grant
    Filed: July 12, 2011
    Date of Patent: May 26, 2015
    Assignee: ROLLS-ROYCE PLC
    Inventors: Simon A. Weeks, Christopher G. Bright
  • Patent number: 9035226
    Abstract: An exoatmospheric vehicle uses a control system that includes a thrust system to provide thrust to control flight of the vehicle. A regenerative heat system is used to preheat portions of the thrust system, prior to their use in control of the vehicle. The heat for preheating may be generated by consumption of a fuel of the vehicle, such as a monopropellant fuel. The fuel may be used to power a pump (among other possibilities), to pressurize the fuel for use by thrusters of the thrust system. The preheated portions of the thrust system may include one or more catalytic beds of the thrust system, which may be preheated using exhaust gasses from the pump. The preheating may reduce the response time of the thrusters that have their catalytic beds preheated. Other thrusters of the thrust system may not be preheated at all before operation.
    Type: Grant
    Filed: January 20, 2014
    Date of Patent: May 19, 2015
    Assignee: Raytheon Company
    Inventors: Wayne C Jouse, Mark S Muktoyuk
  • Patent number: 9027321
    Abstract: Integrated systems and methods for low emission power generation in a hydrocarbon recovery processes are provided. One system includes a control fuel stream, an oxygen stream, a combustion unit, a first power generate on system and a second power generation system. The combustion unit is configured to receive and combust the control fuel stream and the oxygen stream to produce a gaseous combustion stream having carbon dioxide and water. The first power generation system is configured to generate at least one unit of power and a carbon dioxide stream. The second power generation system is configured to receive thermal energy from the gaseous combustion stream and convert the thermal energy into at least one unit of power.
    Type: Grant
    Filed: September 17, 2010
    Date of Patent: May 12, 2015
    Assignee: ExxonMobil Upstream Research Company
    Inventors: Eric D Nelson, Moses Minta, Loren K Starcher, Franklin Mittricker, Omar Angus Sites, Jasper L Dickson
  • Publication number: 20150068188
    Abstract: A turbine engine, an engine structure, and a method of forming an engine structure are provided herein. In an embodiment, an engine structure includes a metal substrate, a thermal barrier coating layer, and a metal silicate protective layer. The thermal barrier coating layer overlies the metal substrate, and the thermal barrier coating layer has columnar grains with gaps defined between the columnar grains. The metal silicate protective layer is formed over the thermal barrier coating layer, and the metal silicate protective layer covers the columnar grains and the gaps between the columnar grains.
    Type: Application
    Filed: September 10, 2013
    Publication date: March 12, 2015
    Inventors: Vladimir K. Tolpygo, Wil Baker
  • Patent number: 8959884
    Abstract: CO2 compression is a main step in carbon capture and storage, which is essential to control global warming. CO2 compressors are powered by electric motors, which increase operational flexibility but require much energy leading to additional expenses, power and efficiency losses. A method is provided for optimized operation of a plant including a power generation unit with a CO2 capture system and compressor with minimum losses during normal operation, allowing flexible part load. The method allows steam from the power unit to drive a steam turbine, which drives the CO2 compressor via an engaged overrunning clutch if a sufficient amount of steam is available from the power unit, and to drive it by the generator, which is used as motor when insufficient steam is available from the power unit. When no or insufficient steam is available the clutch is disengaged and the steam turbine may be at standstill or idling.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: February 24, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Jürgen Hoffmann, Holger Nagel, Hongtao Li
  • Publication number: 20140373503
    Abstract: An automated technique for finishing gas turbine engine blades or vanes by generating a bespoke tooling path for each blade or vane. The bespoke tooling path is generated by scanning the aerofoil surface to generate a 3-D electronic representation of the surface. The 3-D electronic surface is then analysed to identify imperfections or defects, and then a machining path a generated through which the imperfections can be removed. The machining path is determined so as to smoothly blend the surface back to the underlying surface where the imperfections had been present. In this way, the resulting aerofoil, once machined, has optimized aerodynamic performance.
    Type: Application
    Filed: June 11, 2014
    Publication date: December 25, 2014
    Inventor: Roisin Louise HANLON
  • Patent number: 8915089
    Abstract: A system is provided for detecting and controlling flashback and flame holding in a combustor of a gas turbine. The system includes at least one flame indicator disposed in a combustor and at least one detector disposed downstream from the flame indicator. The flame indicator may be configured to produce light when exposed to a flame and the detector may be configured to detect the light produced by the flame indicator.
    Type: Grant
    Filed: January 25, 2010
    Date of Patent: December 23, 2014
    Assignee: General Electric Company
    Inventors: Geoffrey David Myers, Timothy Joseph Rehg, Timothy Andrew Healy, Anthony Wayne Krull
  • Patent number: 8887505
    Abstract: Provided are high-pressure, medium-pressure, and low-pressure turbines; a boiler to generate steam for driving the turbines; a carbon dioxide recovery unit including an absorber that reduces carbon dioxide in combustion flue gas from the boiler by a carbon dioxide absorbent and a regenerator that regenerates an absorbent; a first auxiliary turbine that extracts steam from an inlet of the low-pressure turbine and recovers power by the steam thus extracted; a first steam delivery line to supply discharged steam from the first auxiliary turbine to a reboiler of the regenerator as a heat source; and a controller that controls driving of the first auxiliary turbine while keeping pressure of the discharged steam to be supplied to the reboiler within a tolerance range for the reboiler's optimum pressure corresponding to a fluctuation in an operation load of the boiler.
    Type: Grant
    Filed: December 18, 2009
    Date of Patent: November 18, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Masaki Iijima, Tetsuya Imai, Keiji Fujikawa, Tatsuya Tsujiuchi, Tsuyoshi Oishi, Hiroshi Tanaka
  • Patent number: 8846268
    Abstract: There is provided a combustion apparatus including a gas supply path 1 for supplying a combustible gas, a burner main body 4 for combusting the combustible gas supplied from the gas supply path 1, a cabinet 8 provided to cover the burner main body 4, and a gas cutoff valve 2 provided on the gas supply path 1 on an upstream side of the burner main body 4 and arranged at the outside of the cabinet 8, wherein the burner main body 4 is spacially isolated from the gas cutoff valve 2.
    Type: Grant
    Filed: August 22, 2007
    Date of Patent: September 30, 2014
    Assignee: Panasonic Corporation
    Inventors: Hideo Ohara, Masataka Ozeki
  • Publication number: 20140272639
    Abstract: The present invention generally relates to storing energy in a form that is carbon neutral, storable and transportable, so that it can be used on demand. The present invention provides a process and system for using energy as available to produce carbon from carbon oxide, and then oxidizing the carbon to generate useful energy on demand, while effectively recycling the carbon, oxidant, and carbon oxide used in the process or system. In one embodiment, the present invention effectively stores renewable energy as carbon, transports the carbon, oxidizes the carbon to generate useful energy on demand and recycles the carbon as carbon dioxide. This invention may increase the utilization of renewable energy, especially for electrical power generation, while producing no net carbon dioxide or other air pollutants.
    Type: Application
    Filed: March 14, 2014
    Publication date: September 18, 2014
    Applicant: Zietlow Innovative Engineering and Technology, LLC
    Inventor: Douglas A. ZIETLOW
  • Publication number: 20140260293
    Abstract: A system includes a controller configured to control an operational behavior of a turbine system. The controller includes a droop response system configured to detect one or more operational characteristics of the turbine system as an indication of a frequency variation of an electric power system associated with the turbine system. The droop response system is further configured to generate a response to vary an output of the turbine system in response to the indication of the frequency variation. The controller includes a multivariable droop response correction system configured to determine one or more possible errors associated with the one or more operational characteristics of the turbine system, and to generate a plurality of correction factors to apply to the response generated by the droop response system. The plurality of correction factors is configured to correct the response generated by the droop response system.
    Type: Application
    Filed: March 13, 2013
    Publication date: September 18, 2014
    Applicant: General Electric Company
    Inventors: Yuhui Chen, John Dalton Warren
  • Publication number: 20140215997
    Abstract: A flexible shield for fluid connectors of a gas turbine engine is disclosed. The flexible shield may comprise a flexible sleeve adapted to surround the fluid connector, and a coupling configured to secure the flexible sleeve onto a fluid tube proximate the fluid connector. A gas turbine engine employing such a flexible shield is also disclosed, as is a method of enclosing a fluid connector in a gas turbine engine using such a flexible shield.
    Type: Application
    Filed: September 28, 2012
    Publication date: August 7, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Raphael Lior, Robert J. DeRosa
  • Publication number: 20140202130
    Abstract: A multi-color pyrometry imaging system for a high-temperature asset includes at least one viewing port in optical communication with at least one high-temperature component of the high-temperature asset. The system also includes at least one camera device in optical communication with the at least one viewing port. The at least one camera device includes a camera enclosure and at least one camera aperture defined in the camera enclosure, The at least one camera aperture is in optical communication with the at least one viewing port. The at least one camera device also includes a multi-color filtering mechanism coupled to the enclosure. The multi-color filtering mechanism is configured to sequentially transmit photons within a first predetermined wavelength band and transmit photons within a second predetermined wavelength band that is different than the first predetermined wavelength band.
    Type: Application
    Filed: January 24, 2013
    Publication date: July 24, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jordi Estevadeordal, Nirm Velumylum Nirmalan, Nilesh Tralshawala, Jeremy Clyde Bailey
  • Publication number: 20140182263
    Abstract: The Maphbe Turbine is a system of nozzles, rotors, and energy storage devices used to generate consistent power from intermittent energy sources specifically wind. It uses sails, cables, and poles as a way to form large nozzles and rotors for power generation, these systems can be paired with other renewable sources for co-generation, and can be used for powering pumped storage hydro stations, excess energy can be stored in multi-layer carbon nanotube capacitors. Another application for the invention is offshore floating wind farms to make giant collapsible nozzles and turbines paired with solar, and or wave energy devices.
    Type: Application
    Filed: December 27, 2013
    Publication date: July 3, 2014
    Inventor: Marc Gregory Allinson
  • Publication number: 20140090352
    Abstract: A modular power generation system including a gasification reactor is disclosed for converting fuel, such as, but not limited to, biomass, to syngas to replace petroleum based fuels used in power generation. The system may include a reactor vessel with distinct reaction zones that facilitate greater control and a more efficient system. The system may include a sealing system for a continuous feed system of a gasifier enabling an inlet opening of a feedstock system to remain open yet seal the reactor without a mechanical system. The system may include a syngas heater channeling syngas collected downstream of the carbon layer support and to the pyrolysis reaction zone. The system may also include a syngas separation chamber configured to produce clean syngas, thereby requiring less filtering. The system may further include an agitator drive assembly that prevents formation of burn channels with in the fuel.
    Type: Application
    Filed: September 28, 2012
    Publication date: April 3, 2014
    Applicant: ADAPTIVEARC, INC.
    Inventor: Christian H. A. Juvan
  • Patent number: 8667682
    Abstract: A method of forming an internal combustion engine component having a multi-panel outer wall. The multi-panel outer wall has an inner panel (16) with an inner surface (18) and an outer surface (37). The inner panel outer surface (37) has discrete pockets (23) formed by integral structural ribs (38). Each pocket (23) has a film cooling hole (31) between the pocket (23) and the plenum (20). The method includes: forming dimples (40) in the intermediate panel (22), at least one dimple (40) having a nozzle (29); securing the intermediate panel (22) to the inner panel outer surface (37), thereby enclosing at least one pocket (23); and ensuring a respective dimple (40) having a nozzle (29) protrudes into a respective enclosed pocket (24) and a respective nozzle (29) is configured to direct a respective jet (35) of cooling fluid onto the inner panel outer surface within the respective enclosed pocket (23).
    Type: Grant
    Filed: April 27, 2011
    Date of Patent: March 11, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Jay A. Morrison
  • Patent number: 8631657
    Abstract: Thermodynamic cycles with diluent that produce mechanical power, electrical power, and/or fluid streams for heating and/or cooling are described. Systems contain a combustion system producing an energetic fluid by combusting fuel with oxidant. Thermal diluent is preferably used in the cycle to improve performance, including one or more of power, efficiency, economics, emissions, dynamic and off-peak load performance, temperature regulation, and/or cooling heated components. Cycles include a heat recovery system and preferably recover and recycle thermal diluent from expanded energetic fluid to improve cycle thermodynamic efficiency and reduce energy conversion costs. Cycles preferably include controls for temperatures, pressures, and flow rates within a combined heat and power (CHP) system, and controls for power, thermal output, efficiency, and/or emissions.
    Type: Grant
    Filed: October 10, 2006
    Date of Patent: January 21, 2014
    Assignee: Vast Power Portfolio, LLC
    Inventors: David L. Hagen, Gary Ginter, Alberto Traverso, Bill Goheen, Allan McGuire, Janet Rankin, Aristide Massardo, Ronald L. Klaus
  • Publication number: 20130327010
    Abstract: A wave disc engine apparatus is provided. A further aspect employs a constricted nozzle in a wave rotor channel. A further aspect provides a sharp bend between an inlet and an outlet in a fluid pathway of a wave rotor, with the bend being spaced away from a peripheral edge of the wave rotor. A radial wave rotor for generating electricity in an automotive vehicle is disclosed in yet another aspect.
    Type: Application
    Filed: August 19, 2013
    Publication date: December 12, 2013
    Applicant: Board of Trustees of Michigan State University
    Inventors: Norbert Müller, Janusz Piechna, Guangwei Sun, Pablo-Francisco Parraga
  • Publication number: 20130298522
    Abstract: An assembly for a gas turbine engine, with a gearbox including a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, and a second portion having a second input gear coupled to the turbine shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path. A fan rotor is coupled to the first output gear and a booster rotor is coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. A method of assembling a drive for a fan rotor and a booster rotor in a gas turbine engine is also disclosed.
    Type: Application
    Filed: May 11, 2012
    Publication date: November 14, 2013
    Inventors: Andreas Eleftheriou, David Menheere
  • Patent number: 8578695
    Abstract: An efficient thermal engine is disclosed. In some embodiments, a remainder of energy remaining after an expansion cycle is used to power a subsequent compression cycle. In other embodiments, novel configurations for a larger expansion volume than compression volume are provided. In addition, work of compression may be reduced in a compression cycle, and recovered in an expansion cycle.
    Type: Grant
    Filed: March 5, 2009
    Date of Patent: November 12, 2013
    Inventor: Herbert U. Fluhler
  • Publication number: 20130283756
    Abstract: A manifold assembly for a gas turbine engine includes a mounting plate configured for attachment to a housing structure and a flow plate that is attached to the mounting plate. One or more flow passages are defined between the mounting plate and flow plate.
    Type: Application
    Filed: April 30, 2012
    Publication date: October 31, 2013
    Inventors: Stephanie M. Baker, Marc J. Muldoon, Alessio Pescosolido
  • Patent number: 8567176
    Abstract: A rotating device for producing pressure by expansion of a-pressurized process substance is provided. The rotating device includes a U-channel structure arranged to be rotatable around an axis of a shaft. The U-channel structure includes an expansion point arranged at a periphery of the rotating device, a sinking channel for delivery of the pressurized process substance to the expansion point, a rising channel for delivery of the expanded process substance from the expansion point to a regulating valve for a delivery of the expanded process substance under a higher pressure than that of the pressurized process substance through an outlet channel to an energy recovery device. The rotating device is connected to driving devices in order to rotate the U-channel structure around the axis of the shaft.
    Type: Grant
    Filed: December 27, 2007
    Date of Patent: October 29, 2013
    Assignee: Rotoboost AS
    Inventor: Age Jorgen Skomsvold
  • Patent number: 8561416
    Abstract: A method for managing thermal energy in an internal combustion engine including an exhaust gas recirculation system and an engine cooling system includes recirculating a portion of an exhaust gas through the exhaust gas recirculation system that is in thermal communication with a first side of a thermoelectric device, flowing an engine coolant into thermal communication with a second side of a thermoelectric device, and controlling electric current between an electrical energy storage device and the thermoelectric device to transfer thermal energy between the recirculated exhaust gas and the engine coolant.
    Type: Grant
    Filed: March 29, 2010
    Date of Patent: October 22, 2013
    Assignee: GM Global Technology Operations LLC
    Inventors: Xin He, Alexander Knafl, Russell P. Durrett
  • Publication number: 20130212999
    Abstract: A control system for at least one of steam turbines, gas turbines or power plants includes a sensor system configured to monitor predefined operating parameters, the sensor system including redundant sensors. A central processor arrangement of the control system has an input side configured to receive measurement data from the sensor system and an output side configured to communicate with operation control elements of the turbines or power plants. A sensor side processor circuit is assigned at least to the redundant sensors, the processor circuit being configured to continuously check the sensors for error-free operation, to protect or block the input side of the central processor arrangement from erroneous signals, and to only respectively forward or further process signals from a sensor that has been identified as error-free in one channel.
    Type: Application
    Filed: February 19, 2013
    Publication date: August 22, 2013
    Applicant: ALSTOM TECHNOLOGY LTD
    Inventor: ALSTOM Technology Ltd
  • Publication number: 20130199192
    Abstract: In one embodiment of the present disclosure, a gas turbine system for NOx emission reduction and part load efficiency improvement is described. The system includes a gas turbine having a compressor which receives inlet-air. A direct-contact heat exchanger heats and humidifies the inlet-air before the inlet-air flows to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range. Humidifying the inlet-air can lower NOx emissions from the gas turbine unit.
    Type: Application
    Filed: February 7, 2012
    Publication date: August 8, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jianmin Zhang, Balfang Zuo, Bradly Aaron Kippel
  • Publication number: 20130186100
    Abstract: A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.
    Type: Application
    Filed: January 20, 2012
    Publication date: July 25, 2013
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: William E. Rhoden, Peter L. Jalbert, Rudolph Thomas Beaupre, David Russell Scott
  • Publication number: 20130178677
    Abstract: A method and apparatus convert carbon dioxide into chemical starting materials. Carbon dioxide is isolated from flue gas emitted by a combustion system. An electropositive metal is burned in an atmosphere of isolated carbon dioxide to reduce the carbon dioxide into chemical starting materials.
    Type: Application
    Filed: September 16, 2011
    Publication date: July 11, 2013
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Günter Schmid, Dan Taroata, Elena Arvanitis, Manfred Baldauf, Frank Walachowicz
  • Publication number: 20130152596
    Abstract: A fossil fuel-fired power station having a removal apparatus for carbon dioxide which is located downstream of a combustion facility and through which an offgas containing carbon dioxide may flow is provided. The removal apparatus comprises an absorption unit and a desorption unit. The desorption unit is connected to a renewable energy source.
    Type: Application
    Filed: August 24, 2011
    Publication date: June 20, 2013
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Hermann Kremer, Nicolas Vortmeyer
  • Publication number: 20130111919
    Abstract: The present invention comprises a gas turbine engine and a process for operating a gas turbine engine. A fluid structure receives compressed air from a compressor and extends toward a stationary blade ring in a turbine to discharge the compressed air directly against a surface of the blade ring such that the compressed air impinges on the blade ring surface. The compressed air then passes through at least one opening in the stationary blade ring and into cooling passages of a corresponding row of vanes.
    Type: Application
    Filed: November 8, 2011
    Publication date: May 9, 2013
    Inventors: Abdullatif M. Chehab, David A. Little
  • Patent number: 8429918
    Abstract: A method for generating electrical energy, wherein a carbonaceous fuel is gasified to a combustible gas, the combustible gas being combusted to drive an apparatus chosen from a gas turbine and a gas engine. Relatively hot exhaust gas from the apparatus is passed along a heat exchanger for removing heat from the relatively hot exhaust gas results in relatively cold exhaust gas after passing the heat exchanger. A kaolin or metakaolin-containing sorbent and a source of active free silica are introduced after the apparatus to remove mercury from the relatively hot exhaust gas, the relatively hot exhaust gas having a temperature of at least 800° C.
    Type: Grant
    Filed: April 27, 2012
    Date of Patent: April 30, 2013
    Assignee: Voith Patent GmbH
    Inventor: Joseph J. P. Biermann
  • Patent number: 8365510
    Abstract: Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture.
    Type: Grant
    Filed: August 19, 2009
    Date of Patent: February 5, 2013
    Inventor: Richard H. Lugg
  • Publication number: 20120324859
    Abstract: A heat exchanger is provided for warming fuel prior to introduction of the fuel to an engine, the heat exchanger including: a fuel inlet and a fuel outlet; a heat exchange matrix having heat transfer components past which the fuel flows between said inlet and said outlet and which are arranged to be heated; and swirl inducing means arranged between said inlet and said matrix arranged to cause fuel from said inlet to swirl prior to entering said matrix. By causing the fuel to swirl prior to entering the heat exchange matrix, entrained ice in the fuel can be caused to concentrate at an outer region of the heat exchanger thereby allowing fuel to continue to flow through the heat exchanger to the engine even when ice is present in the fuel.
    Type: Application
    Filed: June 15, 2012
    Publication date: December 27, 2012
    Applicant: ROLLS-ROYCE PLC
    Inventor: Peter FW FOSTER
  • Publication number: 20120317955
    Abstract: A gas turbine engine control system comprising a variable stator vane schedule for normal operation of the gas turbine engine. The system is configured to generate an arm signal indicating potential shaft break. Then the system is configured to alter the variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal. Or the system is configured to limit a response rate of a variable stator vane actuator in response to the arm signal. Or the system is configured to alter the variable stator vane schedule and limit the response rate of the actuator.
    Type: Application
    Filed: June 11, 2012
    Publication date: December 20, 2012
    Applicant: ROLLS-ROYCE PLC
    Inventors: Arthur L. ROWE, Christopher REDFERN
  • Publication number: 20120297791
    Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
    Type: Application
    Filed: May 26, 2011
    Publication date: November 29, 2012
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry
  • Publication number: 20120272521
    Abstract: A method of forming an internal combustion engine component having a multi-panel outer wall. The multi-panel outer wall has an inner panel (16) with an inner surface (18) and an outer surface (37). The inner panel outer surface (37) has discrete pockets (23) formed by integral structural ribs (38). Each pocket (23) has a film cooling hole (31) between the pocket (23) and the plenum (20). The method includes: forming dimples (40) in the intermediate panel (22), at least one dimple (40) having a nozzle (29); securing the intermediate panel (22) to the inner panel outer surface (37), thereby enclosing at least one pocket (23); and ensuring a respective dimple (40) having a nozzle (29) protrudes into a respective enclosed pocket (24) and a respective nozzle (29) is configured to direct a respective jet (35) of cooling fluid onto the inner panel outer surface within the respective enclosed pocket (23).
    Type: Application
    Filed: April 27, 2011
    Publication date: November 1, 2012
    Inventors: Ching-Pang Lee, Jay A. Morrison
  • Publication number: 20120260661
    Abstract: An inlet for removal of a boundary layer from an incoming air flow of an engine is disclosed. The inlet includes at least one compression element proximate to an inlet aperture of the engine. The compression element is selectably moveable between a first position and a second position along an axis. A boundary layer removal aperture is open when the compression element is in the first position and the boundary layer removal aperture is closed when the compression element is in the second position.
    Type: Application
    Filed: April 15, 2011
    Publication date: October 18, 2012
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Sevan Megerian, Chandler Clifton
  • Publication number: 20120167545
    Abstract: A purge system and liquid fuel atomizing system, a system including a purge system and liquid fuel atomizing system, and a method of purging and atomizing are disclosed. The purging involves a first nozzle, a second nozzle, a third nozzle, and a staged compression system having a first stage and a second stage. The first stage is configured to selectively direct a first pressurized fluid stream to the first nozzle and the second nozzle. The second stage is configured to selectively direct a second pressurized fluid stream to the third nozzle.
    Type: Application
    Filed: January 3, 2011
    Publication date: July 5, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Venugopala Durwasula RAJU, Anil Kumar SHARMA, Indrajit MAZUMDER, Bhaskar PEMMI, Rajarshi SAHA
  • Patent number: 8136740
    Abstract: A thermodynamic system that produces mechanical, electrical power, and/or fluid streams for heating or cooling. The cycle contains a combustion system that produces an energetic fluid by combustion of a fuel with an oxidant. A thermal diluent may be used in the cycle to improve performance, including but not limited to power, efficiency, economics, emissions, dynamic and off-peak load performance, and/or turbine inlet temperature (TIT) regulation and cooling heated components. The cycle preferably includes a heat recovery system and a condenser or other means to recover and recycle heat and the thermal diluent from the energetic fluid to improve the cycle thermodynamic efficiency and reduce energy conversion costs. The cycle may also include controls for temperatures, pressures, and flow rates throughout the cycle, and controls power output, efficiency, and energetic fluid composition.
    Type: Grant
    Filed: August 25, 2008
    Date of Patent: March 20, 2012
    Assignee: Vast Power Portfolio, LLC
    Inventors: David L. Hagen, Gary Ginter, Alberto Traverso, Bill Goheen, Allan McGuire, Janet Rankin, Aristide Massardo, Ronald L. Klaus
  • Publication number: 20120031067
    Abstract: Disclosed is a turbulated arrangement of thermoelectric elements for utilizing waste heat generated from a turbine engine. The turbulated arrangement of thermoelectric elements is located within the turbine casing at a heat exhaust end of the turbine engine. The turbulated arrangement of thermoelectric elements convert heat exhaust generated from the turbine engine into electrical energy. In one embodiment, the electrical energy generated from the turbulated arrangement of thermoelectric elements can be used to power electrical components located about the turbine engine.
    Type: Application
    Filed: August 3, 2010
    Publication date: February 9, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Hariharan Sundaram, Mayur Abhay Keny, Kathleen Blanche Morey
  • Publication number: 20120017598
    Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly.
    Type: Application
    Filed: July 11, 2011
    Publication date: January 26, 2012
    Applicant: ICR TURBINE ENGINE CORPORATION
    Inventors: James B. Kesseli, Matthew Stephen Baldwin
  • Publication number: 20110314788
    Abstract: The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (la) comprises a means for shifting the axis (la-la) of the blower (9a) transverse to the axis (La-La) of the hot flow generator (4a).
    Type: Application
    Filed: January 5, 2010
    Publication date: December 29, 2011
    Applicant: AIRBUS OPERATIONS (S.A.S.)
    Inventor: Jacques Hervé Marche
  • Publication number: 20110302901
    Abstract: A method of optimizing operation of a furnace to control emission within a system. Each furnace zone inside of the furnace is associated with at least one exhaust zone. A signal indicative of an amount of byproduct exiting the furnace through at least one of the exhaust zones is received from one or more of the sensors. Based on this signal, an offending furnace zone is identified from among the plurality of furnace zones, the offending furnace zone including an oxygen level contributing to the amount of the byproduct. A relative adjustment of at least one of an amount of oxygen being introduced into the offending furnace zone, and an angular orientation of an oxygen injector introducing oxygen into the offending furnace zone relative to a focal region within the furnace can be initiated. The furnace may have structure to perform the method and may be part of a system.
    Type: Application
    Filed: June 9, 2010
    Publication date: December 15, 2011
    Applicant: General Electric Company
    Inventors: Guang Xu, Neil Colin Widmer
  • Patent number: 8051637
    Abstract: A heat absorbing radiator and a gas turbine engine or a reciprocating piston engine are used to recapture and reconvert wasted heat energies into electric power and finally into hydrogen-deuterium fuel by having the engine's tailpipes submerged in cold compressed air inside the heat absorbing radiator pipes in reverse air flow to further drive the same engine. In order to capture fusion heat energy a hydrogen bomb is detonated in deep ocean to catch the flames by the water and the hot water energizes compressed air inside heat absorbing radiator pipes. In order to produce fusion energy an electric arc is passed thru/across liquid or gaseous deuterium by an electro-plasma torch and by a sparkplug in an internal combustion engine, or by detonating a dynamite inside liquid deuterium. Diamond is produced by placing carbon inside a hydrogen bomb which is then detonated in deepwater. Deuterium fusion flame is used first in smelting glass into large structural sizes before running an engine.
    Type: Grant
    Filed: July 27, 2005
    Date of Patent: November 8, 2011
    Inventor: Gaudencio Aquino Labrador
  • Publication number: 20110138765
    Abstract: Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture.
    Type: Application
    Filed: August 19, 2009
    Publication date: June 16, 2011
    Applicant: SONIC BLUE AEROSPACE, INC.
    Inventor: Richard H. Lugg
  • Patent number: 7946843
    Abstract: A method of and a plant for combusting carbonaceous fuel, the method including the steps of introducing particulate oxygen selective sorbent, such as a perovskite type material, into an adsorption reactor of the combustion plant to form a first particle bed in the adsorption reactor, fluidizing the first particle bed by an oxygen-containing first fluidizing gas to adsorb oxygen from the fluidizing gas to the sorbent, conveying oxygen-rich sorbent from the adsorption reactor to a combustion reactor of the combustion plant to form a second particle bed in the combustion reactor, fluidizing the second particle bed by an oxygen-deficient second fluidizing gas to desorb oxygen from the sorbent, so as to produce free oxygen gas, and introducing carbonaceous fuel into the combustion reactor to oxidize the fuel with the free oxygen gas.
    Type: Grant
    Filed: July 20, 2007
    Date of Patent: May 24, 2011
    Assignee: Foster Wheeler North America Corp.
    Inventors: Zhen Fan, Horst Hack, Andrew Seltzer, Archibald Robertson
  • Publication number: 20110108663
    Abstract: The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter (4), a second energy converter (5) and a propulsion unit (1). The first energy converter (4) provides first propulsion energy, and the second energy converter (5) provides second propulsion energy. The first energy converter (4) and the second energy converter (5) are adapted to provide the first propulsion energy and the second propulsion energy to the propulsion device (1).
    Type: Application
    Filed: November 26, 2007
    Publication date: May 12, 2011
    Applicant: AIRBUS DEUTSCHLAND GMBH
    Inventor: Andreas Westenberger
  • Patent number: 7921631
    Abstract: In at least one embodiment of the present invention, a method of recovering energy from a FCC unit having a reactor and a regenerator for overall CO2 reduction is provided. The method comprises cooling syngas to a predetermined low temperature to define cooled syngas. A turbo-expander including a first compressor is provided. The turbo-expander train is configured to combust and expand gas to drive the first compressor. The cooled syngas is compressed with the first compressor to define compressed syngas. A first stream of gas comprising CO2 and a second stream of gas comprising CO are separated from the compressed syngas. O2 and the first and second streams of gas are introduced to the turbo-expander train. The first stream of gas is expanded and the second stream of gas is combusted and expanded with the O2 to recover energy, driving the first compressor and producing the syngas.
    Type: Grant
    Filed: September 22, 2010
    Date of Patent: April 12, 2011
    Assignees: UOP LLC, BP Corporation North America Inc.
    Inventor: Brian W. Hedrick
  • Publication number: 20100326039
    Abstract: A gas turbine includes a disk rotatable about a rotational axis, when turbine rotor blades for receiving combustion gas obtained by burning fuel are connected to the side periphery, and energy of the combustion gas received by the turbine rotor blades is transmitted, and a radial passage that, in a cross-section at a virtual curved plane that is a curved plane about the rotational axis and in which distances from all points on the curved plane to the rotational axis are all equal, is a hole formed to include a portion having a shape in which the length in the circumferential direction of the disk is longer than the length in the direction parallel to the rotational axis, and is formed in the disk from the side of the rotational axis toward the outside of the disk.
    Type: Application
    Filed: December 24, 2008
    Publication date: December 30, 2010
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kenichi Arase, Shinya Hashimoto
  • Publication number: 20100290911
    Abstract: A turbine rotor (1) for a gas turbine with a one-piece compressor housing (11) or a compressor housing (11) which is divided in a first plane, a one-piece turbine housing (12) connected to the compressor housing (11) or a turbine housing (12) which is divided in a second plane different from the first plane comprises a compressor area which includes at least two compressor disks (2.1-2.5) and a turbine area which includes at least one turbine disk (13.1, 13.2). The compressor disks and turbine disks are clamped together by a tie rod arrangement which includes at least one tie rod (6) which has a first fastening area, a second fastening area for clamping at least two compressor disks between the first fastening area and the second fastening area, and a third fastening area for clamping at least one turbine disk.
    Type: Application
    Filed: November 3, 2008
    Publication date: November 18, 2010
    Applicant: Man Diesel & Turbo SE
    Inventors: Emil Aschenbruck, Ralf Müller, Michael Blaswich