Patents Examined by Michael B Mantyla
  • Patent number: 9470149
    Abstract: A heating and cooling system for inlet air of a turbine compressor. The heating and cooling system may include a thermal energy storage tank charging loop, a cooling loop in communication with the thermal energy storage charging loop, and a heating loop in communication with the cooling loop and the inlet air of the turbine compressor.
    Type: Grant
    Filed: December 11, 2008
    Date of Patent: October 18, 2016
    Assignee: General Electric Company
    Inventors: Abbas Motakef, Peter Feher
  • Patent number: 9347374
    Abstract: A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The mid-turbine frame is in fluid communication with the heat exchanger. The conditioned airflow is communicated through the passageway and is received by the first nozzle assembly to condition gas turbine engine hardware.
    Type: Grant
    Filed: February 27, 2012
    Date of Patent: May 24, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Ioannis Alvanos
  • Patent number: 9328695
    Abstract: A gas turbine engine (10) includes a fan (14), a nacelle (28) arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage (30) downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow (1) from the fan. A nozzle (40) associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: May 3, 2016
    Assignee: United Technologies Corporation
    Inventors: Constantine Baltas, Amr Ali
  • Patent number: 9328666
    Abstract: An example turbofan engine restarting system includes a core nacelle housing, a compressor, and a turbine. The core nacelle is disposed within a fan nacelle. A bypass flowpath downstream from the turbofan is arranged between the two nacelles. A controller is programmed to manipulate the nozzle exit area of the bypass flowpath to facilitate startup of the engine. In one example, the controller manipulates the nozzle exit area using hinged flaps in response to an engine shutdown condition. The flaps open and close to adjust the nozzle exit area and the associated bypass flow rate, the mass flow rate of the air through the core nacelle and the rotational speed of the compressor rotor.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: May 3, 2016
    Assignee: United Technologies Corporation
    Inventors: Ashok K. Jain, Michael Winter
  • Patent number: 9316117
    Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: April 19, 2016
    Assignee: United Technologies Corporation
    Inventors: Paul K. Sanchez, Kalpendu J. Parekh, William A. Daniels, John S. Tu
  • Patent number: 9303523
    Abstract: A sensor communication system includes an electromagnetic waveguide disposed adjacent to at least one component of a machine. The electromagnetic waveguide can be configured to convey a fluid within the machine. The sensor communication system can also include a sensor assembly, which includes a sensor operable to sense at least one condition and a transmitter at least partially positioned in the electromagnetic waveguide. The transmitter can be operatively coupled to the sensor and be operable to emit a signal corresponding to the at least one condition sensed by the sensor. The sensor communication system can also include a receiver at least partially positioned in the electromagnetic waveguide and operable to wirelessly receive the signal emitted by the transmitter.
    Type: Grant
    Filed: June 3, 2011
    Date of Patent: April 5, 2016
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Rigoberto Rodriguez, Mark Blackwelder
  • Patent number: 9297306
    Abstract: An exhaust gas recirculation system that includes an exhaust gas recirculation regulator operatively connectable to a turbomachine system, and regulating a predetermined amount of exhaust gas to be recirculated. The exhaust gas recirculation system further includes a measuring unit that measures fuel composition of incoming fuel, and a control unit connected to the EGR regulator and the measuring unit, and determining a Wobbe Index and/or reactivity of the incoming fuel based on the measured fuel composition and determining the predetermined amount of exhaust gas to be recirculated based on the determined Wobbe Index and/or reactivity.
    Type: Grant
    Filed: September 11, 2008
    Date of Patent: March 29, 2016
    Assignee: General Electric Company
    Inventors: George Martin Gilchrist, III, Stanley Frank Simpson, Hasan Karim
  • Patent number: 9297313
    Abstract: A control apparatus for angling guide vanes of a torque converter is provided and includes a modeling unit configured to receive current condition data, to determine a current input power supplied by a starting motor from the current condition data and to output a result of the determination as a control signal and a controller, which is coupled to the modeling unit and thereby receptive of the control signal. The controller is configured to execute a comparison of the current input power with a rating of the starting motor and to angle the guide vanes of the torque converter at an angle in accordance with a result of the comparison.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: March 29, 2016
    Assignee: General Electric Company
    Inventors: Jason Dean Fuller, Justin Aaron Allen, Karl Dean Minto
  • Patent number: 9291102
    Abstract: A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: March 22, 2016
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Timothy A. Fox, Reinhard Schilp
  • Patent number: 9267434
    Abstract: A gas turbine engine has a fan, a compressor section, a combustor, and a turbine section. The fan delivers a portion of air into the compressor, and into a duct, as bypass air. A bleed air system bleeds a quantity of air from the compressor into a chamber at least at low power conditions of the engine. The bleed air system has an opening which may be selectively closed to block bleed air, or opened to allow bleed flow from the compressor into the chamber. A heat exchanger is positioned such that a first surface of the heat exchanger is contacted by bypass air in the duct, and a second surface of the heat exchanger is contacted by bleed air when the bleed air system directs air from the compressor into the chamber.
    Type: Grant
    Filed: January 29, 2012
    Date of Patent: February 23, 2016
    Assignee: United Technologies Corporation
    Inventors: Xiaojun Campbell, Thomas G. Phillips, Kathleen R. Phillips
  • Patent number: 9254729
    Abstract: The part load method controls delivery of diluent fluid, fuel fluid, and oxidant fluid in thermodynamic cycles using diluent, to increase the Turbine Inlet Temperature (TIT) and thermal efficiency in part load operation above that obtained by relevant art part load operation of Brayton cycles, fogged Brayton cycles, or cycles operating with some steam delivery, or with maximum steam delivery. The part load method may control the TIT at the design level by controlling one or both of liquid and/or gaseous fluid water over a range from full load to less than 45% load. This extends operation to lower operating loads while providing higher efficiencies and lower operating costs using water, steam and/or CO2 as diluents, than in simple cycle operation.
    Type: Grant
    Filed: September 2, 2008
    Date of Patent: February 9, 2016
    Assignee: Vast Power Portfolio, LLC
    Inventors: L. Allan McGuire, Ian Wylie, David L. Hagen
  • Patent number: 9255484
    Abstract: An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.
    Type: Grant
    Filed: March 16, 2011
    Date of Patent: February 9, 2016
    Assignee: General Electric Company
    Inventors: David William Cihlar, Patrick Benedict Melton, David Leach, Kevin Weston McMahan
  • Patent number: 9243507
    Abstract: A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.
    Type: Grant
    Filed: January 9, 2012
    Date of Patent: January 26, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Patrick Benedict Melton
  • Patent number: 9200592
    Abstract: A gas turbine engine includes a high spool, a low spool mechanically connected to a fan, a gear system, an actuator, and a starter. The gear system is actuable to engage and disengage the low spool to and from the high spool. The actuator is connected to the gear system for selectively engaging and disengaging the gear system. The starter is connected to the low spool and can drive rotation of the high spool through the low spool when the gear system is engaged.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: December 1, 2015
    Assignee: United Technologies Corporation
    Inventors: Andrew P. Berryann, Gabriel L. Suciu
  • Patent number: 9181899
    Abstract: A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.
    Type: Grant
    Filed: August 27, 2008
    Date of Patent: November 10, 2015
    Assignee: General Electric Company
    Inventors: Mustafa Dindar, Scott Andrew Burton, Keith Edward James Blodgett, Richard David Cedar
  • Patent number: 9151227
    Abstract: A fuel injector for a gas turbine engine may include an injector housing extending along a longitudinal axis and configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a flow path for a fuel air mixture to the combustor extending longitudinally within the injector housing, and a gallery for liquid fuel encircling the flow path. The gallery may include a plurality of fuel spokes that are configured to deliver liquid fuel from the gallery to the flow path. The gallery may extend from a feed end to a terminal end that overlaps the feed end. The feed end may be a region where liquid fuel enters the gallery and the terminal end may be a region where the gallery terminates.
    Type: Grant
    Filed: November 10, 2010
    Date of Patent: October 6, 2015
    Assignee: Solar Turbines Incorporated
    Inventors: John Frederick Lockyer, Christopher Zdzislaw Twardochleb, Mario Eugene Abreu
  • Patent number: 9140455
    Abstract: A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.
    Type: Grant
    Filed: January 4, 2012
    Date of Patent: September 22, 2015
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Russell Pierson DeForest, Patrick Benedict Melton
  • Patent number: 9127598
    Abstract: Ambient air is compressed into a compressed ambient gas flow with a main air compressor. The compressed ambient gas flow having a compressed ambient gas flow rate is delivered to a turbine combustor and mixed with a fuel stream having a fuel stream flow rate and a portion of a recirculated low oxygen content gas flow to form a combustible mixture. The combustible mixture is burned and forms the recirculated low oxygen content gas flow that drives a turbine. A portion of the recirculated low oxygen content gas flow is recirculated from the turbine to the turbine compressor using a recirculation loop. The compressed ambient gas flow rate and the fuel stream flow rate are adjusted to achieve substantially stoichiometric combustion. An excess portion, if any, of the compressed ambient gas flow is vented. A portion of the recirculated low oxygen content gas flow is extracted using an extraction conduit.
    Type: Grant
    Filed: August 25, 2011
    Date of Patent: September 8, 2015
    Assignee: General Electric Company
    Inventors: Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, NoƩmie Dion Ouellet
  • Patent number: 9121610
    Abstract: Disclosed is a combustor casing with an inner casing which defines a combustion chamber, an outer casing spaced apart from the inner casing for defining a passage between the inner and the outer casing, first and second effusion holes arranged in the inner casing, and dividing ribs connecting the inner and outer casings and forming at least first and second volumes for receiving part of a flow injected into the passage.
    Type: Grant
    Filed: May 5, 2009
    Date of Patent: September 1, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Kam-Kei Lam
  • Patent number: 9109540
    Abstract: A cascade thrust reverser for an airplane dual flow jet engine nacelle is provided that includes a front frame holding a plurality of cascades, a cowling slidably mounted between a direct jet position and a reverse jet position. The cowl includes a substantially annular diaphragm that is placed edge-to-edge with the front frame and radially inside said cascades when said cowl is located in the direct jet position. Thrust reversal flaps are pivotably mounted onto the diaphragm, and cylinders for actuating the cowl are also provided. Upstream ends of the cylinders are mounted on a stationary portion of the nacelle, and the downstream ends of the cylinders are mounted on an upstream edge of the diaphragm.
    Type: Grant
    Filed: November 19, 2012
    Date of Patent: August 18, 2015
    Assignee: AIRCELLE
    Inventor: Guy Bernard Vauchel