Patents Examined by Kyle Thomas
  • Patent number: 9932898
    Abstract: A pipe arrangement for a turbomachine is provided having a fluid pipe for guiding fluids and a coupling element for coupling the fluid pipe to a temperature affected component. The coupling element is configured to provide a first connection between the coupling element and the component by a first end of the coupling element. The coupling element provides also a second connection between the coupling element and a first surface section of the fluid pipe by a second end of the coupling element. Furthermore, the coupling element has a sleeve portion surrounding a second surface section of the fluid pipe and being spaced apart to the second surface section of the fluid pipe. A fluid inlet or outlet arrangement is also provided having such a pipe arrangement and also a gas turbine engine having such a pipe arrangement.
    Type: Grant
    Filed: May 21, 2013
    Date of Patent: April 3, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventor: Trevor Milne
  • Patent number: 9932856
    Abstract: Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.
    Type: Grant
    Filed: November 22, 2014
    Date of Patent: April 3, 2018
    Assignee: General Electric Company
    Inventors: Hua Zhang, Douglas Scott Byrd, David Terry Trayhan, Jr.
  • Patent number: 9926797
    Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.
    Type: Grant
    Filed: January 22, 2015
    Date of Patent: March 27, 2018
    Assignee: United Technologies Corporation
    Inventors: Steven D. Porter, Jonathan Lemoine, Kevin Zacchera
  • Patent number: 9909761
    Abstract: A wall assembly of a combustor for a turbine engine includes a shell and a liner and a sealing interface structure. A cooling cavity is defined between the shell and liner and the sealing interface structure functions to minimize leakage out of the cooling cavity. The sealing interface structure may have a sealing width that is equal to or greater than twice the thickness of the liner and/or may include a chamber located between longitudinal segments of the sealing interface structure that inhibits leakage.
    Type: Grant
    Filed: April 7, 2015
    Date of Patent: March 6, 2018
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka, Timothy S. Snyder
  • Patent number: 9903589
    Abstract: A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure.
    Type: Grant
    Filed: August 27, 2014
    Date of Patent: February 27, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul Allan Hucker, Alan Philip Geary, Anthony John Moran, Jonathan Mark Gregory
  • Patent number: 9890739
    Abstract: Provided are methods and systems for measuring and controlling nozzle areas of variable area fan nozzles. A control system attached to a nozzle may include a cable having one end connected to a linear displacement measuring device, such as a string potentiometer. The other end of the cable may be connected to a petal. A reference portion of the cable extends across multiple petals of the nozzle and, in some embodiments, substantially parallel to the nozzle circumference. The linear displacement measuring device measures any changes in the length of this reference portion as the petals actuate outwardly or inwardly during operation of the nozzle. The output of the linear displacement measuring device may be used to control actuators that move the petals. In some embodiments, potentiometer's output may be combined with one or more outputs from other sensors, such as a linear variable differential transducer and/or thermocouple.
    Type: Grant
    Filed: March 23, 2015
    Date of Patent: February 13, 2018
    Assignee: The Boeing Company
    Inventors: Jason Joseph Jackowski, Matthew A. Carpenter, Kent Edmund Karnofski
  • Patent number: 9890714
    Abstract: An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine. Additionally, a method of automated extended turndown of a GT engine to find a minimum load is provided.
    Type: Grant
    Filed: January 30, 2015
    Date of Patent: February 13, 2018
    Inventors: Sumit Soni, Nicolas Roger Demougeot, Peter John Stuttaford
  • Patent number: 9879610
    Abstract: A pneumatic system 131 for use with gas turbine engines 10 and aircraft 100. The pneumatic system 131 comprises a first engine core compressor bleed offtake in the form of an engine handling bleed offtake 140, and a second engine core compressor bleed offtake in the form of first and second cabin bleed offtake 132, 134, the handling bleed being configured to supply higher pressure air than the cabin offtakes 132, 134. The system 131 comprises a turbocompressor 144 comprising an air compressor 148 driven by a turbine 146. The handling bleed offtake 140 is in fluid communication with the turbocompressor air turbine 146 to thereby drive the air turbine 146, and the cabin bleed offtakes 132, 134 are in fluid communication with the turbocompressor air compressor 148 such that air from the offtakes 132, 134 is compressed by the turbocompressor air compressor 148.
    Type: Grant
    Filed: October 15, 2014
    Date of Patent: January 30, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Thierry Moes
  • Patent number: 9863320
    Abstract: The invention relates to a heat exchanger of an air circulation channel of a turbomachine, the heat exchanger being configured so as to have fluid to be cooled passing through it and including a plurality of fins protruding from a support surface, the heat exchanger being characterized in that each fin includes a base and a preferably continuous leading face which extends axially from the base in the air circulation direction while tapering from upstream to downstream along an axis parallel with the support surface.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Imane Ghazlane, Gabriela Philippart
  • Patent number: 9856791
    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: Grant
    Filed: August 19, 2013
    Date of Patent: January 2, 2018
    Assignee: Board of Trustees of Michigan State University
    Inventors: Norbert Müller, Janusz Piechna, Guangwei Sun, Pablo-Francisco Parraga
  • Patent number: 9850816
    Abstract: An inlet air conditioning system for a gas turbine includes an inlet duct for the with an air flow path to provide inlet air to the gas turbine; evaporative cooling media disposed in the air flow path; a water chiller; and a circulation pump that circulates water through the water chiller and the evaporative media in series. The chiller is configured to chill the water to below ambient wet-bulb temperature before the water is circulated to the evaporative cooling media. A power plant includes a gas turbine including a compressor, a combustion system, and a turbine section; a load; and the inlet air conditioning system.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: December 26, 2017
    Assignee: General Electric Company
    Inventors: JIanmin Zhang, Brad Aaron Kippel
  • Patent number: 9835335
    Abstract: A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector, an ignitor unit and an air blast injector. The pilot burner device has a pilot body with a pilot surface facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume, wherein the fuel outlet is arranged at the pilot surface. The ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The air blast injector is adapted for injecting an air blast into the inner volume, wherein the air blast injector includes an air blast outlet arranged at the pilot surface such that the air blast is injectable in the direction to the fuel outlet and the ignitor unit for directing the fuel to the ignitor unit.
    Type: Grant
    Filed: November 11, 2013
    Date of Patent: December 5, 2017
    Inventor: Timothy Dolmansley
  • Patent number: 9822707
    Abstract: A vent for use in a gaseous fuel supply circuit of a gas turbine is provided. The vent includes an inlet in flow communication with the gaseous fuel supply circuit, a first outlet in flow communication with the gaseous fuel supply circuit and configured to release gaseous fuel at atmospheric pressure, a first valve coupled between the inlet and the first outlet, wherein the first valve includes a second outlet configured to channel the gaseous fuel towards a combustion device. The system also includes a second valve coupled between the inlet and the second outlet, and a control device configured to selectively open and close the first and second valves based on a pressure of the gaseous fuel.
    Type: Grant
    Filed: December 18, 2012
    Date of Patent: November 21, 2017
    Assignee: General Electric Company
    Inventors: Yann Tapie, Cedric Vasselon, Olivier Schweiger, Olivier Chapuis
  • Patent number: 9822670
    Abstract: A power generation system may include: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied. The first integral compressor has a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor. A turbo-expander may be operatively coupled to the second gas turbine system. Control valves may control flow of the excess air flow from the first gas turbine system to at least one of the second gas turbine system and the turbo-expander, and flow of a discharge of the turbo-expander to an inlet of at least one of the first integral compressor and the second compressor.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: November 21, 2017
    Assignee: General Electric Company
    Inventors: Sanji Ekanayake, Thomas John Freeman, Kihyung Kim, Alston Ilford Scipio, Leslie Yung Min Tong
  • Patent number: 9803867
    Abstract: A premix pilot nozzle includes a tip portion having a downstream surface that extends between a downstream end of an inner wall of the tip portion and a downstream end of an outer wall of the tip portion. The downstream end of the inner wall terminates axially upstream from the downstream end of the outer wall. At least a portion of the downstream surface is curvilinear. The tip portion further comprises a plurality of axially extending premix tubes annularly arranged about the tip portion. Each premix tube defines a premix flow passage through the tip portion. Each premix tube also includes an outlet that is axially offset from the downstream surface.
    Type: Grant
    Filed: April 21, 2015
    Date of Patent: October 31, 2017
    Inventor: Jason Thurman Stewart
  • Patent number: 9797312
    Abstract: A supporting structure for a gas turbine engine includes an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings. The radial elements have an airfoil shape with a leading edge directed towards the inlet side of the supporting structure, a trailing edge directed towards the outlet side of the supporting structure, and two opposite sides connecting the leading edge and the trailing edge. At least one of the radial elements includes a gas passage arrangement configured to lead a separate bleeding gas flow from the supporting structure. The gas passage arrangement includes a radially extending gas channel arranged inside the radial element and at least one opening in communication with the gas channel. The at least one opening is arranged at one of the two opposite sides of the radial element.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: October 24, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Goran Johnsson, Rickard Samuelsson
  • Patent number: 9790859
    Abstract: A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
    Type: Grant
    Filed: October 27, 2014
    Date of Patent: October 17, 2017
    Inventor: James W. Norris
  • Patent number: 9677471
    Abstract: One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator.
    Type: Grant
    Filed: November 10, 2014
    Date of Patent: June 13, 2017
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yoshitaka Takahashi, Kazuhiko Sato, Yasushi Takeda