Patents Examined by Arun Goyal
  • Mid-turbine frame rod and turbine case flange
    Patent number: 10060291
    Abstract: A turbine section of a gas turbine engine includes a first turbine supported for rotation about an axis, a second turbine spaced axially aft of the for first turbine section for rotation about the axis, and a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine. A first case surrounds the first turbine and a second case surrounding the second turbine and attached to the first case. The mid-turbine frame is disposed between the first turbine section and the second turbine section and includes at least one support structure extending through an interface between the first turbine case and the second turbine case.
    Type: Grant
    Filed: February 18, 2014
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventor: Keshava B. Kumar
  • Air biasing system in a gas turbine combustor
    Patent number: 10054313
    Abstract: A combustor (10) including: a first premix main burner (14) comprising a first swirler airfoil section (38); a second premix main burner (15) comprising a second swirler airfoil section (40); and a supply air reversing region upstream of the premix burners (14), (15). The first swirler airfoil section (38) and the second swirler airfoil section (40) are effective to impart swirl to a first airflow and a second airflow characterized by a same swirl number as the airflows exit respective burners (14), (15). The combustor (10) is effective to generate a first airflow volume through the first premix main burner (14) that is different than a second airflow volume through the second premix main burner (15).
    Type: Grant
    Filed: July 8, 2010
    Date of Patent: August 21, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Juan Enrique Portillo Bilbao, Scott M. Martin, David M. Ritland
  • System and method for high efficiency power generation using a carbon dioxide circulating working fluid
    Patent number: 10047671
    Abstract: The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.
    Type: Grant
    Filed: January 23, 2015
    Date of Patent: August 14, 2018
    Assignee: 8 Rivers Capital, LLC
    Inventors: Rodney John Allam, Glenn William Brown, Jr., Miles R. Palmer
  • Combustor wall with tapered cooling cavity
    Patent number: 10047958
    Abstract: A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.
    Type: Grant
    Filed: October 6, 2014
    Date of Patent: August 14, 2018
    Assignee: United Technologies Corporation
    Inventors: Nurhak Erbas-Sen, Frank J. Cunha
  • Starting of aircraft engine
    Patent number: 10041412
    Abstract: A multi-engine system 10 for use on an aircraft 14 is disclosed. The system 10 may comprise a first aircraft engine 16A and a second aircraft engine 16B configured to drive at least one device 12 of the aircraft 14. A starter 20 may be coupled to one of the first and second aircraft engines 16A, 16B to assist starting of the one of the first and second aircraft engines 16A, 16B. An energy source 24 may be configured to deliver energy to the starter 20 at a rapid rate during rapid starting of the one of the first and the second aircraft engines 16A, 16B, the rapid rate being higher than a regular rate used during regular starting of the one of the first and the second aircraft engines 16A, 16B. The energy source 24 may comprise at least one supercapacitor.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: August 7, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kevin Allan Dooley, Keith Morgan
  • Method and system for starting up an aircraft turbomachine by real-time regulation of air flow
    Patent number: 10041414
    Abstract: The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: August 7, 2018
    Assignees: AIRBUS OPERATIONS S.L., AIRBUS OPERATIONS SAS, GENERAL ELECTRIC COMPANY
    Inventors: Patrick Zaccaria, Philippe Chareyre, Pio Fernandez-Lopez, Carlos Casado-Montero
  • Geared turbofan with three co-rotating turbines
    Patent number: 10036351
    Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan rotor through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine rotate in the same direction.
    Type: Grant
    Filed: April 2, 2012
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Geared turbofan with three turbines all co-rotating
    Patent number: 10036350
    Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis, Thomas J. Praisner
  • Combustion chamber for a gas turbine
    Patent number: 10024540
    Abstract: A combustion chamber for a gas turbine is provided. The combustion chamber comprises at least one first and one second jet carrier, of which at least one is provided for injecting an operating gas in the combustion chamber such that waste gas formed in the flame zone thereof is circulated to a mixing zone of the first jet carrier. In order to achieve a compact combustion chamber, the jet carriers are positioned in relation to each other such that waste gas from the flame zone of the first jet carrier flows directly to the mixing zone of the second jet carrier.
    Type: Grant
    Filed: January 24, 2008
    Date of Patent: July 17, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Peter Kaufmann, Werner Krebs
  • System and method for high efficiency power generation using a carbon dioxide circulating working fluid
    Patent number: 10018115
    Abstract: The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: July 10, 2018
    Assignee: 8 Rivers Capital, LLC
    Inventors: Rodney John Allam, Miles R. Palmer, Glenn William Brown, Jr., Jeremy Eron Fetvedt, Brock Alan Forrest
  • Gas turbine engine control for rotor bore heating
    Patent number: 10018120
    Abstract: A gas turbine engine comprises a compressor rotor including blades and a disk, with a bore defined radially inwardly of the disk, and a combustor. A tap directs the products of combustion first to a valve and then into the bore of the disk. At least two temperature sensors sense a temperature of the products of combustion downstream of the valve. A control compares sensed temperatures from the at least two temperature sensors to ensure the at least two temperature sensors are functioning properly. The sensed temperatures are utilized to control the valve. A method of operating a gas turbine engine is also disclosed.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: July 10, 2018
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Paul W. Duesler
  • Combustion chamber and a method of mixing fuel and air in a combustion chamber
    Patent number: 9995488
    Abstract: A combustion chamber including a first fuel injector and a second fuel injector, the first and second fuel injectors being arranged to inject fuel into a mainstream flow of air with the second fuel injector arranged downstream of the first fuel injector. A method of mixing fuel and air in a combustion chamber, including injecting fuel into a mainstream flow of air with a first fuel injector; injecting fuel into the mainstream flow of air with a second fuel injector, which is arranged downstream of the first fuel injector; injecting fuel into the mainstream flow with the first fuel injector such that the resulting mixture between the first and second fuel injectors has an equivalence ratio less than the lean flame stability limit; and injecting fuel into the mainstream flow with the second fuel injector such that a combustion zone is provided downstream of the second fuel injector.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: June 12, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Stephen C. Harding
  • Geared axial multistage expander device, system and method
    Patent number: 9995143
    Abstract: Method, system and axial multistage expander including a casing and a plurality of stages. A stage includes a stator part connected to the casing and having plural statoric airfoils, and a rotor part configured to rotate relative to the stator part and having plural rotoric airfoils. The axial multistage expander also includes a support mechanism connected to the casing and configured to rotatably support the rotor part. Rotoric airfoils of at least one stage of the plurality of stages are configured to rotate with a speed different from rotoric airfoils of the other stages. The stator part, the rotor part and the support mechanism of the plurality of stages are provided inside the casing.
    Type: Grant
    Filed: February 18, 2015
    Date of Patent: June 12, 2018
    Inventors: Michele D'Ercole, Simone Billi, Stefania Della Gatta
  • Planetary gear system arrangement with auxiliary oil system
    Patent number: 9995174
    Abstract: A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: June 12, 2018
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
  • Turbine engine with a combustion chamber outer flange of sandwich type
    Patent number: 9988982
    Abstract: A turbine engine has inner and outer annular covers containing an annular combustion chamber and an annular nozzle. The combustion chamber is held in position inside the outer annular cover between two radial holder rings that are nested at least in part one within the other and that have their radially outer first ends secured to the outer annular cover by fasteners and their radially inner second ends in the form of combs holding in position between them a transverse rim of the annular combustion chamber so as to enable a cooling stream to flow towards the annular nozzle and so as to hold the annular combustion chamber axially while leaving it free to move at least radially.
    Type: Grant
    Filed: February 24, 2015
    Date of Patent: June 5, 2018
    Assignee: SNECMA
    Inventor: Frederic Delaunay
  • Damper for combustion oscillation damping in a gas turbine
    Patent number: 9970659
    Abstract: The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length Lneck of the neck is equal or greater than a maximum distance lmax that a hot gas ingested from the combustion chamber reaches in the neck. The maximum distance lmax is determined according to the following equation: l max = ? t 1 t 2 ? U - p ^ ? ? ? U ? ? ? ? sin ? ( ? ? ? t ) ? ? d ? ? t . With the solution of the present invention, the damper used to damping combustion oscillation may prevent hot gas ingestion during normal operations by uniquely determining the dimensions of the neck connecting the resonator cavity and the combustion chamber.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: May 15, 2018
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Bruno Schuermans, Mirko Ruben Bothien
  • Tank and method for manufacturing same
    Patent number: 9963997
    Abstract: The present invention relates to a method for manufacturing a tank (1) comprising a main body (4) with several compartments (7), a base (6) closing the lower part of the main body (4), and a cover (5) closing the upper part of the main body (4), said method comprising the following steps: shaping sheets to produce the parts making up the tank (1); assembling each of the component parts by butt welding in order to produce the tank (1).
    Type: Grant
    Filed: May 22, 2014
    Date of Patent: May 8, 2018
    Assignee: Safran Aero Boosters SA
    Inventors: Albert Cornet, Stéphane Bougelet
  • Anaerobic hybrid propulsion device with fuel present in the form of divided solids
    Patent number: 9957919
    Abstract: An anaerobic propulsion device of hybrid type. The propulsion device includes a combustion chamber into which an oxidant is injected thereto comes into contact with a fuel. The chamber includes an orifice, notably a nozzle, to inject the combustion gases. The fuel takes the form of solids divided into granules, typically grains, powder or beads. The propulsion device further includes a segregation device arranged between a reservoir for granules of solid fuel, and the combustion chamber. The segregation device is configured to prevent granules of fuel in solid form from passing between the reservoir and the combustion chamber. The segregation device includes orifices to allow the passage of the fuel, once the fuel has become pasty, liquid or vaporized.
    Type: Grant
    Filed: September 10, 2013
    Date of Patent: May 1, 2018
    Assignee: AIRBUS DEFENCE AND SPACE SAS
    Inventor: Christophe Figus
  • Fuel manifold cooling flow recirculation
    Patent number: 9957891
    Abstract: Cooling flow recirculation in fuel manifolds, such as fuel manifolds associated with gas turbine engines is disclosed. An example system for jet pump driven recirculation of manifold cooling flow according to at least some aspects of the present disclosure may include a flow split valve having a spool valve disposed therein, the flow split valve having a pilot manifold and a main manifold attached thereto; a jet pump fluidically coupled to the pilot manifold, the jet pump being arranged to drive recirculation of a cooling flow through the main manifold via a cooling flow circuit in a pilot only mode of operation; and/or a fuel nozzle in fluid communication with the pilot manifold and the main manifold.
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: May 1, 2018
    Assignee: General Electric Company
    Inventor: Frederick Ehrwulf Van Alen
  • Hybrid air blast fuel nozzle
    Patent number: 9939157
    Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: April 10, 2018
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Duane Douglas Thomsen