Patents Examined by Ted Kim
  • Combustor and gas turbine
    Patent number: 9926845
    Abstract: A combustor according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: March 27, 2018
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Sosuke Nakamura, Yoshikazu Matsumura, Hikaru Katano, Kenta Taniguchi, Hiroyuki Yamasaki
  • Generating device for aircraft
    Patent number: 9890839
    Abstract: An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).
    Type: Grant
    Filed: April 4, 2012
    Date of Patent: February 13, 2018
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Tatsuhiko Goi, Kenichiro Tanaka, Koji Watanabe, Isao Fujii
  • Hybrid slinger combustion system
    Patent number: 9874148
    Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: January 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Fan nozzle drive systems that lock thrust reversers
    Patent number: 9863367
    Abstract: Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.
    Type: Grant
    Filed: November 1, 2013
    Date of Patent: January 9, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Michael J. Burghdoff, Jerry Edward Farstad
  • Combined cycle power plant with flue gas recirculation
    Patent number: 9828912
    Abstract: An exemplary method for the operation of a CCPP with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases as well as a plant designed to operate is disclosed. To allow a high flue gas recirculation ration (rFRG) an imposed combustion inhomogeneity ratio (ri) is used for flame stabilization. The imposed combustion inhomogeneity ratio (ri) is controlled as function of the flue gas recirculation rate (rFRG) and/or combustion pressure. Oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustor is admixed to enhance operatability.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: November 28, 2017
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Marta De La Cruz Garcia, Thierry Lachaux, Andre Burdet, Jaan Hellat
  • Eliminatin of unfavorable outflow margin
    Patent number: 9816394
    Abstract: A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow.
    Type: Grant
    Filed: March 21, 2014
    Date of Patent: November 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Timothy S. Snyder
  • Casing body through which hot gases can flow and comprising an inner heat shield
    Patent number: 9810154
    Abstract: A casing body for a hot gas flow includes an outer casing body having a hot gas side with a precisely prepared locating surface. A pin-type retainer is disposed on the locating surface, and an inner heat shield is disposed at a distance from the hot gas side of the outer casing body and fastened to the retainer.
    Type: Grant
    Filed: August 23, 2011
    Date of Patent: November 7, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Marc Rauch, Peter Oskar Baldischweiler
  • Engine and combustion system
    Patent number: 9777627
    Abstract: One embodiment of the present invention is a unique engine. Another embodiment of the present invention is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 29, 2011
    Date of Patent: October 3, 2017
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Philip H. Snyder
  • Swirl reducing gas turbine engine recuperator
    Patent number: 9766019
    Abstract: A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: September 19, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu, Darius Jehangir Karanjia, Daniel Van Den Ende
  • Airflow modulation system and method
    Patent number: 9752453
    Abstract: The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: September 5, 2017
    Assignee: NORTHROP GRUMMAN SYSTEMS CORPORATION
    Inventors: George D. Rupp, Trajaen J. Troia
  • Helical cross flow (HCF) pulse detonation engine
    Patent number: 9726080
    Abstract: A helical cross flow pulse detonation engine.
    Type: Grant
    Filed: May 2, 2013
    Date of Patent: August 8, 2017
    Assignee: Orbital ATK, Inc.
    Inventors: Daniel P. Guinan, Christopher D. Gettinger
  • Turbojet engine nacelle with variable ventilation outlet cross section
    Patent number: 9670798
    Abstract: A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions.
    Type: Grant
    Filed: April 25, 2013
    Date of Patent: June 6, 2017
    Assignee: AIRCELLE
    Inventors: Guy Bernard Vauchel, Laurence Lemains
  • Turbomachine with fan(s) for aircraft, with mobile jet nozzle
    Patent number: 9556744
    Abstract: A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: January 31, 2017
    Assignee: SNECMA
    Inventors: Sebastien Dron, Nicolas Jerome Jean Tantot
  • Assembly including a reverse thrust device and system for actuating said device
    Patent number: 9518535
    Abstract: A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl.
    Type: Grant
    Filed: November 30, 2012
    Date of Patent: December 13, 2016
    Assignee: AIRCELLE
    Inventors: Guy Bernard Vauchel, Patrick Gonidec
  • Combustor for gas turbine engine
    Patent number: 9513008
    Abstract: A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.
    Type: Grant
    Filed: September 14, 2015
    Date of Patent: December 6, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Jeffrey Verhiel, Parthasarathy Sampath
  • Fluid pressure amplifier
    Patent number: 9494146
    Abstract: A housing 10 defining a duct 11 for fluid flow contains a cylinder arrangement 18-20 mounted in or at an outlet end of the duct. An input piston 30 is exposed to the fluid flow through the duct and an obturator member 21 is mounted in the duct 11 and arranged to periodically close the duct downstream of the input piston 30 such that the body of fluid flowing through the duct applies an increased pressure to the input piston. Resulting movement of the input piston can be used to directly provide mechanical power, generate electricity, or provide compression of a volatile fluid which, when ignited, provides thrust through rapid exit of combustion products.
    Type: Grant
    Filed: June 17, 2011
    Date of Patent: November 15, 2016
    Assignee: WATE POWERED TECHNOLOGIES LIMITED
    Inventor: Frederick Philip Selwyn
  • Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
    Patent number: 9476355
    Abstract: A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: October 25, 2016
    Assignee: SIEMENS ENERGY, INC.
    Inventors: David A. Little, Gerard McQuiggan, David L. Wasdell
  • Combustion chamber
    Patent number: 9470419
    Abstract: The invention relates to a combustion chamber for burning an air-fuel mixture, a gas mixture or a gas-liquid mixture, including an outer casing; a flame tube located inside the outer casing and provided with an inner space, whereby the outer casing and the flame tube form an annular channel therebetween, the flame tube including flow apertures which penetrate through its casing and interconnect the annular channel and the inner space of the flame tube; a cover part arranged in inlet ends of the outer casing and the flame tube and provided with flow apertures opening up into the annular channel; a combustion air inlet part which is arranged in an outer surface of the cover part and which is in connection with the flow apertures of the cover part; a fuel jet located in the cover part and extending inside the flame tube for feeding fuel into the flame tube.
    Type: Grant
    Filed: November 22, 2012
    Date of Patent: October 18, 2016
    Assignee: RMV TECH OY
    Inventor: Markus Viitamäki
  • System and method for heating fuel in a combined cycle gas turbine
    Patent number: 9470145
    Abstract: A system for heating fuel in a combined cycle gas turbine includes a fuel heat exchanger downstream from a turbine outlet, and the fuel heat exchanger has an exhaust gas inlet, an exhaust gas outlet, a fuel inlet, and a fuel outlet. A first exhaust gas plenum has a first exhaust gas inlet connection between the turbine outlet and a heat exchanger and a first exhaust gas outlet connection upstream from the exhaust gas inlet. A second exhaust gas plenum has a second exhaust gas inlet connection downstream from at least a portion of the heat exchanger and a second exhaust gas outlet connection upstream from the exhaust gas inlet.
    Type: Grant
    Filed: October 15, 2012
    Date of Patent: October 18, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: David Wesley Ball, Jr., Korey Frederic Rendo, Dean Matthew Erickson, Diego Fernando Rancruel, Leslie Yung-Min Tong
  • Pivoting blocker door for thrust reverser
    Patent number: 9447749
    Abstract: A thrust reverser includes a translating sleeve and a blocking door assembly that includes two, three, or four blocker door segments. The translating sleeve is movable axially with respect to a fan case and a core cowl between a cruise position and a thrust reversal position. The blocker door segments are positioned adjacent an inner wall of the translating sleeve in the cruise position, and are pivotable to a position in which the blocker door segments substantially block the bypass duct in the thrust reversal position. Each blocker door segment is connected to the translating sleeve at transverse ends by a pair of support bearings that establish a pivot axis along an arc chord of the blocker door segment.
    Type: Grant
    Filed: April 2, 2013
    Date of Patent: September 20, 2016
    Assignee: Rohr, Inc.
    Inventor: Norman John James