With Ignition Device Patents (Class 60/39.821)
  • Patent number: 11859555
    Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.
    Type: Grant
    Filed: January 12, 2023
    Date of Patent: January 2, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jasmin Turcotte, Ioan Sabau
  • Patent number: 11773784
    Abstract: A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle includes a nozzle body that defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor with a flame outlet opens into the main flow passage of the fuel nozzle for issuing flame into the main flow passage. The flame outlet meets the main flow passage at a position that is downstream of the fuel outlet with respect to the downstream direction along the injection axis.
    Type: Grant
    Filed: October 12, 2021
    Date of Patent: October 3, 2023
    Assignee: Collins Engine Nozzles, Inc.
    Inventors: Jason Ryon, Lev A. Prociw, Brandon Phillip Williams
  • Patent number: 11578867
    Abstract: A combustor of an embodiment includes: a combustor casing; a combustor liner which is provided in the combustor casing and combusts a fuel and an oxidant to produce a combustion gas; a pipe-shaped member provided to penetrate the combustor casing and the combustor liner; a heat-resistant glass which is provided on the combustor casing side in the pipe-shaped member and closes the pipe-shaped member; a laser light supply mechanism which irradiates an interior of the combustor liner through the heat-resistant glass and an interior of the pipe-shaped member with a laser light; and a contact prevention mechanism which prevents a combustion gas in the combustor liner from coming into contact with the heat-resistant glass.
    Type: Grant
    Filed: February 2, 2021
    Date of Patent: February 14, 2023
    Assignee: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION
    Inventors: Yasunori Iwai, Masao Itoh, Yuichi Morisawa, Yoshihisa Kobayashi, Shinju Suzuki
  • Patent number: 11566565
    Abstract: An embodiment of an ignition system for a gas turbine engine includes a high pressure engine case, a torch ignitor disposed at least partially within the high pressure engine case, the torch ignitor having a combustion chamber oriented about a torch axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The ignition system also includes an access hatch configured to allow access through a high pressure engine case to the cap and to seal against the high pressure engine case when not accessing the cap. An embodiment of a method includes removing a hatch from a high pressure engine case to open a hatch opening, performing maintenance on a torch ignitor that is inside the high pressure engine case by accessing the torch ignitor through the hatch opening, replacing the hatch to close the hatch opening after completion of maintenance on the torch ignitor.
    Type: Grant
    Filed: December 23, 2020
    Date of Patent: January 31, 2023
    Assignee: Collins Engine Nozzles, Inc.
    Inventors: Jason Ryon, Lev A. Prociw, Brandon Phillip Williams
  • Patent number: 11519334
    Abstract: An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.
    Type: Grant
    Filed: July 31, 2017
    Date of Patent: December 6, 2022
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Yimin Huang, Abdul Khan, Thomas Edward Johnson, Heath M. Ostebee, Jayaprakash Natarajan
  • Patent number: 11466657
    Abstract: To suppress a failure of ignition of a fuel caused by a spark plug while suppressing wear of an electrode of the spark plug in an internal combustion engine. A control device 1 for an internal combustion engine includes an ignition control unit that controls energization of an ignition coil 300 that applies electric energy to a spark plug 200 that discharges in a cylinder 150 of an internal combustion engine 100 to ignite a fuel. The ignition control unit continuously transmits a first pulse signal (pulse signal for corona discharge) to an igniter connected to the ignition coil 300 before dielectric breakdown between electrodes of the spark plug 200, and continuously transmits a second pulse signal (pulse signal for arc discharge) to the igniter after the dielectric breakdown between the electrodes of the spark plug 200 to control the energization of the ignition coil 300. At this time, a period of the pulse signal for corona discharge is shorter than a period of the pulse signal for arc discharge.
    Type: Grant
    Filed: October 4, 2019
    Date of Patent: October 11, 2022
    Assignee: Hitachi Astemo, Ltd.
    Inventor: Eiichirou Ohata
  • Patent number: 11391462
    Abstract: The invention relates to a combustion chamber comprising: a duct (722) with a recess for a spark plug (13) emerging into an inner space of the combustion chamber, and a plug guide mounted on the duct so as to be movable transversely relative to the axis of the duct. The duct is crossed by openings (722b) which, parallel to the axis of the duct, are staggered in a plurality of rows (74a, 74b . . . ) over the height (H) of the duct, with at least some of the openings individually having a diameter of 0.2 to 0.6 mm.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: July 19, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Joseph Jean Marie Burguburu
  • Patent number: 11098901
    Abstract: In a gas turbine combustor, a sectional shape in a radial direction of either one of an inner peripheral surface of a second inner tube member and an outer peripheral surface of a first inner tube member, in a fitting portion of a crossfire tube assembly, has a plurality of small-curvature portions having a curvature smaller than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from the center of the sectional shape. This configuration ensures the crossfire tube assembly is cooled, and the Possibility of thermal deformation or fire damage is lowered, without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly of the gas turbine combustor.
    Type: Grant
    Filed: November 7, 2018
    Date of Patent: August 24, 2021
    Assignee: Mitsubishi Power, Ltd.
    Inventors: Hirofumi Okazaki, Tomomi Koganezawa, Hirokazu Takahashi
  • Patent number: 10823398
    Abstract: A torch igniter and a method of igniting a torch flame. An example embodiment includes a body including an oxidizer inlet configured to facilitate oxidizer flow through the body toward an output end of the body. The body includes a group of fuel inlet passages configured to distribute fuel in a direction tangential to the oxidizer flow through the body to create a swirling fuel-oxidizer mixture. A sparking element can be mounted on the body to produce a spark in the path of the swirling fuel-oxidizer mixture to ignite the mixture. The output end of the body is configured to emit a torch flame when the fuel-oxidizer mixture is ignited. Thus, a swirl torch igniter is configured for oxidizer and fuel flow through the igniter body to create an internal swirling fuel-oxidizer mixture to be ignited by a sparking element.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: November 3, 2020
    Assignee: Board of Regents, The University of Texas System
    Inventors: Ahsan R. Choudhri, Norman D. Love, Jr., Luis E. Sanchez, Charles S. Hill
  • Patent number: 10753283
    Abstract: A combustor heat shield has a heat shield body having a first surface configured to face a combustor shell and an opposed second surface configured to face towards the combustion gases in the combustion chamber. A dilution or igniter hole is defined in the heat shield body. An array of circumferentially spaced-apart cooling holes is provided around the at least one dilution or igniter hole. The cooling holes are oriented to locally deliver a swirl of cooling air around an axis of the dilution or igniter hole. The cooling holes are angled relative to the heat shield body and extend from an inlet on the first surface to an outlet on the second surface. The outlet is positioned closer to a perimeter of the dilution or igniter hole than the inlet.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: August 25, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Si-Man Amy Lao
  • Patent number: 10451282
    Abstract: A fuel nozzle includes an outer body extending parallel to a centerline axis, having a generally cylindrical exterior surface, forward and aft ends, and a plurality of openings through the exterior surface. The fuel nozzle further includes an inner body inside the outer body, cooperating with the outer body to define an annular space, and a main injection ring inside the annular space, the main injection ring including fuel posts extending therefrom. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap which communicates with the annular space. There is a circumferential main fuel gallery in the main injection ring, and a plurality of main fuel orifices, wherein each orifice communicates with the main fuel gallery and extends through one of the fuel posts.
    Type: Grant
    Filed: December 23, 2014
    Date of Patent: October 22, 2019
    Assignee: General Electric Company
    Inventors: Michael Anthony Benjamin, Joshua Tyler Mook, Sean James Henderson, Ramon Martinez
  • Patent number: 10240788
    Abstract: A combustion system includes an electrically actuated flame location control mechanism.
    Type: Grant
    Filed: August 17, 2018
    Date of Patent: March 26, 2019
    Assignee: CLEARSIGN COMBUSTION CORPORATION
    Inventors: Douglas W. Karkow, Joseph Colannino, Igor A. Krichtafovitch, Robert E. Breidenthal, Christopher A. Wiklof
  • Patent number: 10228136
    Abstract: A combustor assembly for a gas turbine engine is includes a liner and a combustor dome formed of a ceramic matrix composite material. The combustor dome and liner together define at least in part a combustion chamber. The combustor dome extends along a circumferential direction and defines one or more openings, the combustor dome is configured to receive one or more fuel-air injector hardware assemblies in or through the one or more openings.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: David Andrew Hannwacker, Stephen John Howell
  • Patent number: 10197281
    Abstract: A combustion system for a gas turbine includes a combustion chamber having an end section and a pre-combustion section extending from the end section, a swirler device, an optional pilot burner device and a light emitting arrangement. Main fuel is injectable by the swirler device into an inner volume of the pre-combustion section. The main flame using main fuel is producible inside the inner volume. The pilot burner device is mounted to the end section of the combustion chamber such that a pilot fuel is injectable by the pilot burner device into the inner volume of the pre-combustion section, wherein a pilot flame using the pilot fuel is producible inside the inner volume for stabilizing the main flame. The light emitting arrangement emits an electromagnetic radiation into the inner volume, such that an energy input is generatable by the electromagnetic radiation for stabilizing the pilot flame and/or the main flame.
    Type: Grant
    Filed: January 23, 2014
    Date of Patent: February 5, 2019
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Timothy Dolmansley, Jonathan May, Herman Ruijsenaars
  • Patent number: 10151489
    Abstract: A combustor arrangement with a front panel, a combustor liner, and a carrier structure element is provided for carrying the front panel and the combustor liner, wherein the combustor arrangement further includes a fastening system for connecting the front panel, the combustor liner, and the carrier structure element to one another. The fastening system includes at least one elastic connection element, the latter being fixedly connected to the carrier structure element and extending therefrom to the combustor liner and to the front panel. The elastic connection element is further fixedly connected to the combustor liner and/or the front panel such as to clamp the front panel, the combustor liner, and the carrier structure element to one another in a substantially fluid tight manner.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: December 11, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Ulrich Rathmann, Naresh Aluri
  • Patent number: 10132498
    Abstract: Aspects of the disclosure are directed to a liner associated with a combustor of an aircraft engine, comprising: a thermal barrier coating, and a base metal, wherein the thermal barrier coating comprises a contoured surface on a flowpath side proximate to an exit of a hole formed by the thermal barrier coating and the base metal.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: November 20, 2018
    Assignee: United Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 10088159
    Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Nurhak Erbas-Sen, James B. Hoke, John S. Tu, Monica Pacheco-Tougas
  • Patent number: 9954343
    Abstract: A casing for a laser spark plug, in particular, of an internal combustion engine of a motor vehicle, or of a stationary engine; the casing including at least one casing part and a combustion chamber window joined to the casing part to form a seal at least regionally; characterized in that at least one sealing element, whose coefficient of thermal expansion at an operating temperature of the laser spark plug is greater than the coefficient of thermal expansion of the casing part at the operating temperature of the laser spark plug, is provided between the casing part and the combustion chamber window.
    Type: Grant
    Filed: February 4, 2016
    Date of Patent: April 24, 2018
    Assignee: ROBERT BOSCH GMBH
    Inventors: Joerg Engelhardt, Dieter Wolz, Juergen Raimann, Pascal Woerner, Martin Weinrotter
  • Patent number: 9897319
    Abstract: The present disclosure relates combustor configurations for a gas turbine engine. In one embodiment, a combustor includes a combustor shell enclosing a first area of free space, and an igniter for the combustor shell, the igniter including a distal end. The combustor also includes one or more elements configured to retain the igniter and to interface with the combustor shell, wherein the igniter is retained that the distal end of the igniter is recessed from the first area of free space. According to another embodiment, a combustor configuration may include one or more elements configured to retain an igniter and interface with the combustor shell, wherein the one or more elements define a boundary between the combustor shell and one or more elements, and wherein the igniter is retained within the one or more elements such that the distal end of the igniter is recessed from the boundary.
    Type: Grant
    Filed: February 25, 2015
    Date of Patent: February 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Robert M. Sonntag, Michael Youssef, Edward B. Harris, Richard A. Long
  • Patent number: 9869277
    Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: January 16, 2018
    Assignee: Foret Plasma Labs, LLC
    Inventor: Todd Foret
  • Patent number: 9863261
    Abstract: A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing. The fairing is engaged by the probe to prevent circumferential movement of the fairing relative to the casing.
    Type: Grant
    Filed: December 29, 2012
    Date of Patent: January 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Conway Chuong, Matthew Budnick
  • Patent number: 9856849
    Abstract: A laser ignition system has: at least one arrangement for producing a pulsed laser beam; and at least one arrangement for focusing the produced pulsed laser beam onto a focus zone, e.g., in order to ignite a combustible gas mixture in an internal combustion engine or a burner. The laser ignition system is designed to produce a pulsed laser beam having a normed fluence volume greater than 0.1.
    Type: Grant
    Filed: February 7, 2014
    Date of Patent: January 2, 2018
    Assignee: ROBERT BOSCH GMBH
    Inventors: Heiko Ridderbusch, Joern Ostrinsky
  • Patent number: 9822708
    Abstract: A system for a gas turbine engine includes an igniter event conductor. The igniter event conductor has a first portion adjacent an igniter of the engine and in a combustion chamber of the engine and a second portion apart from the igniter and apart from the combustion chamber. The conductor is adapted to conduct an aspect of an igniter event at the igniter from the first portion to the second portion. A sensor is coupled to the second portion of the conductor to sense the aspect of the igniter event.
    Type: Grant
    Filed: May 6, 2014
    Date of Patent: November 21, 2017
    Assignee: Woodward, Inc.
    Inventors: Daniel S. Burke, Jeffrey Taylor Stewart, Jim Causey, Michael Hackenberg, Bruce Harrar
  • Patent number: 9803863
    Abstract: A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.
    Type: Grant
    Filed: May 13, 2015
    Date of Patent: October 31, 2017
    Assignee: Solar Turbines Incorporated
    Inventors: Crosby Hayhurst Johnson, Yong Weon Kim, Ted Edwin Groocock
  • Patent number: 9765698
    Abstract: A flexible bellows assembly is disclosed for sealing an engine igniter for use with an engine. The bellows assembly includes a mounting arrangement that is operable to be secured to a combustor diffuser instead of the combustor liner. The bellows has a component that impinges upon a surface of the combustor liner so as to form a sealed chamber between a metal diffuser and a ceramic combustion liner. An igniter passes through the sealed chamber and provides ignition to the combustor.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: September 19, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Russell Bennett, Michael S. Bell
  • Patent number: 9742156
    Abstract: A casing for a laser spark plug, in particular, of an internal combustion engine of a motor vehicle, or of a stationary engine; the casing including at least one casing part and a combustion chamber window joined to the casing part to form a seal at least regionally; characterized in that at least one sealing element, whose coefficient of thermal expansion at an operating temperature of the laser spark plug is greater than the coefficient of thermal expansion of the casing part at the operating temperature of the laser spark plug, is provided between the casing part and the combustion chamber window.
    Type: Grant
    Filed: September 24, 2012
    Date of Patent: August 22, 2017
    Assignee: ROBERT BOSCH GMBH
    Inventors: Joerg Engelhardt, Dieter Wolz, Juergen Raimann, Pascal Woerner, Martin Weinrotter
  • Patent number: 9581088
    Abstract: A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds. The control system includes a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds. The control system further includes a controller which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split.
    Type: Grant
    Filed: June 4, 2014
    Date of Patent: February 28, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Yong Qin, Andrew Stevenson
  • Patent number: 9423131
    Abstract: An air management arrangement for a late lean injection combustor system includes a combustor liner defining a combustor chamber. Also included is a sleeve surrounding at least a portion of the combustor liner, the combustor liner and the sleeve defining a cooling annulus for routing a cooling airflow from proximate an aft end of the combustor liner toward a forward end of the combustor liner. Further included is a cooling airflow divider region configured to split the cooling airflow into a first cooling airflow portion and a second cooling airflow portion, wherein the first cooling airflow portion is directed to at least one primary air-fuel injector, wherein the second cooling airflow portion is directed to at least one lean-direct injector extending through the sleeve and the cooling annulus for injection of the second cooling airflow portion into the combustor chamber.
    Type: Grant
    Filed: October 10, 2012
    Date of Patent: August 23, 2016
    Assignee: General Electric Company
    Inventor: Wei Chen
  • Patent number: 9394830
    Abstract: An igniter tube assembly includes an igniter, an igniter tower with a radially extending portion, a ferrule with a radially extending portion, and a retainer with a radially extending portion. The ferrule and retainer capture the radially extending portion of the igniter tower and sealing surface provides an area for the ferrule to interface with the igniter tower. The igniter moves relative to the casing in which it is secured while a fluid seal between the igniter and ferrule controls air flow.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: July 19, 2016
    Assignee: Rolls-Royce Corporation
    Inventor: Kelly J. McCormick
  • Patent number: 9360217
    Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.
    Type: Grant
    Filed: March 18, 2013
    Date of Patent: June 7, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia, Christopher Paul Willis, Ronnie Ray Pentecost
  • Patent number: 9328925
    Abstract: A cross-fire tube purging arrangement includes a cross-fire tube extending from proximate a combustor chamber to proximate an adjacent combustor chamber for fluidly coupling the combustor chamber and the adjacent combustor chamber. Also included is a compressed air supply arrangement for selectively delivering a compressed air to the cross-fire tube, the compressed air supply arrangement comprising a regulating component for controlling delivery of the compressed air to the cross-fire tube.
    Type: Grant
    Filed: November 15, 2012
    Date of Patent: May 3, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Daniel Doyle Vandale
  • Patent number: 9255549
    Abstract: A laser ignition device is used for igniting propellants in a rocket engine. The laser ignition device has an injector housing with passages for flowing gaseous hydrogen and liquid oxygen to injector elements which mix the hydrogen and oxygen in a combustion chamber. A laser ignition system assembly is inserted through the housing. The propellants in the housing keep the housing and the laser ignition system assembly cool. A laser beam entering the laser ignition system assembly via a fiber optic cable passes though a lens for diverging the laser beam and a second lens for converging the beam. A portion of the laser ignition system assembly extends beyond the injector housing face plate into the combustion chamber of the rocket engine.
    Type: Grant
    Filed: July 21, 1997
    Date of Patent: February 9, 2016
    Inventor: William S. Brown
  • Patent number: 9121608
    Abstract: A combustor system for use in a turbine engine is provided. The turbine engine includes turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween. The combustor system includes a first combustor assembly and a second combustor assembly. The first combustor assembly is coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly. The first combustor assembly is oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine assembly inlet. The second combustor assembly is coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly.
    Type: Grant
    Filed: December 29, 2011
    Date of Patent: September 1, 2015
    Assignee: General Electric Company
    Inventors: Ahmed Mostafa Elkady, Christian Lee Vandervort, Narendra Joshi, Sherif Mohamed
  • Patent number: 9091445
    Abstract: A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
    Type: Grant
    Filed: December 3, 2010
    Date of Patent: July 28, 2015
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Nicolas Christian Raymond Leblond, Guillaume Sevi, Denis Jean Maurice Sandelis, Christophe Pieussergues
  • 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: 9021781
    Abstract: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged.
    Type: Grant
    Filed: January 4, 2013
    Date of Patent: May 5, 2015
    Assignee: General Electric Company
    Inventors: Kaitlin Marie Graham, James Scott Flanagan, Jeffrey Scott LeBegue
  • Patent number: 8997453
    Abstract: An exemplary igniter assembly for a turbomachine includes an igniter extending along an axis from an igniting end portion to an opposing end portion. The igniting end of the igniter is configured to be received within a bore of a tube. An annular seal restricts flow between the igniting end and the tube.
    Type: Grant
    Filed: June 29, 2012
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventor: Hannes A. Alholm
  • Patent number: 8978355
    Abstract: Variable rate ignition method and system that take advantage of knowledge and analysis of environmental conditions and/or operational conditions. A variable ignition rate for igniting the engine permits an optimal use of the igniters and thereby prolongs their life as well as its associated maintenance schedule. Operating costs and durability are also enhanced. Furthermore, flexibility is enhanced since any changes to the method of determining the best spark rate can be made through update in the software of the engine controller instead of change in the hardware (e.g., the exciter).
    Type: Grant
    Filed: November 29, 2007
    Date of Patent: March 17, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Richard Robert Kudrna, Danielle Methot
  • Patent number: 8966879
    Abstract: An acoustic resonance igniter uses gas expanding through a nozzle to form a sonic, or under-expanded supersonic, jet directed against the opening of a blind resonance cavity in a central body, setting up a high-frequency sonic resonance which heats the gas within the cavity. A pintle extends coaxially with the nozzle and injects liquid propellant into the jet. The liquid propellant ignites with the heated gas within the resonance cavity forming combustion gases. The combustion gases flow through openings in a flange which supports the resonance cavity into a combustion chamber in the same direction as the gas jet flows. The liquid propellant is injected from within the support flange in the direction of combustion gas flow to film cool the combustion chamber wall and the flange and the central body supported by the flange. The acoustic resonance igniter may form a rocket engine ignition torch or a RCS thruster.
    Type: Grant
    Filed: February 15, 2012
    Date of Patent: March 3, 2015
    Assignee: Orbital Technologies Corporation
    Inventor: Scott M. Munson
  • Patent number: 8959925
    Abstract: A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a first combustion can is extinguished during a full load operation of the gas turbine, adjusting a fuel ratio between the fuel nozzles in each can, delivering a richer fuel mixture to the fuel nozzles nearest to the cross-fire tubes, generating a cross-fire from the second combustion can to the first combustion can, detecting a recovery of the turbine load, and adjusting the fuel ratio to the normal balanced fuel distribution between the fuel nozzles in each can.
    Type: Grant
    Filed: January 18, 2012
    Date of Patent: February 24, 2015
    Assignee: General Electric Company
    Inventors: Bryan Wesley Romig, Derrick Walter Simons, Venkat Narra
  • Publication number: 20140366505
    Abstract: A head assembly for an ignition system includes a head block and a plurality of igniters seated in the head block. The head block has an issue aperture and defines an issue axis, and is configured and adapted for sealably coupling with an igniter combustion chamber. The igniters are arranged about the issue aperture and include respective ignition members arranged obliquely with respect to the issue axis for igniting fuel exiting the issue aperture irrespective to orientation of the ignition system.
    Type: Application
    Filed: January 31, 2014
    Publication date: December 18, 2014
    Applicant: DELAVAN INC
    Inventors: Lev A. Prociw, Jason A. Ryon, Steven J. Myers
  • Publication number: 20140352275
    Abstract: An igniter tube assembly includes an igniter, an igniter tower with a radially extending portion, a ferrule with a radially extending portion, and a retainer with a radially extending portion. The ferrule and retainer capture the radially extending portion of the igniter tower and sealing surface provides an area for the ferrule to interface with the igniter tower. The igniter moves relative to the casing in which it is secured while a fluid seal between the igniter and ferrule controls air flow.
    Type: Application
    Filed: December 19, 2013
    Publication date: December 4, 2014
    Applicant: Rolls-Royce Corporation
    Inventor: Kelly J. McCormick
  • Patent number: 8881526
    Abstract: A steam turbine system uses a laser to instantaneously vaporize water in a nozzle within a turbine. This steam is then used to rotate the turbine. Thus, the turbine system does not require an external boiler. The steam turbine system may be used in either an open system, where the steam passing through the turbine is not condensed and reused, or a closed system, where the steam passing through the turbine is condensed and reused.
    Type: Grant
    Filed: September 9, 2011
    Date of Patent: November 11, 2014
    Assignee: Bastian Family Holdings, Inc.
    Inventors: William A. Bastian, II, Elizabeth Sobota
  • Patent number: 8875484
    Abstract: A turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, the wall forming a body of revolution. The guide means includes a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means includes a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug.
    Type: Grant
    Filed: November 18, 2010
    Date of Patent: November 4, 2014
    Assignee: SNECMA
    Inventors: Dominique Maurice Jacques Lains, Nicolas Christian Raymond Leblond, Christophe Pieussergues
  • Patent number: 8863495
    Abstract: An ignition/chemical reaction promotion/flame holding device and a high-performance speed-type internal combustion engine using this device are provided, whereby ignition and the spreading and holding of flames can be dramatically improved in a gas turbine, a ram machine, a rocket engine, or another speed-type internal combustion engine. An ignition/chemical reaction promotion/flame holding device of a speed-type internal combustion engine comprises a spark plug for preparing charged particles in a predetermined location in a combustor of the speed-type internal combustion engine, and a microwave oscillator and antenna for inducing plasma with a working fluid in the combustor as a starter material by irradiating the charged particles and their surrounding vicinity with microwave pulses; wherein a region in which sufficient conditions for performing combustion are met is formed in the combustor by supplying an active chemical species produced from the working fluid by the effect of the plasma.
    Type: Grant
    Filed: July 12, 2008
    Date of Patent: October 21, 2014
    Assignee: Imagineering, Inc.
    Inventor: Yuji Ikeda
  • Patent number: 8839600
    Abstract: An igniter for a rocket engine or motor comprising a combustion chamber with a solid fuel, an inlet for supplying an oxidizer to the combustion chamber to ignite the solid fuel and an outlet for discharging exhaust gas, wherein the igniter is arranged to discharge exhaust gas to the rocket engine for igniting the rocket engine. The igniter can be used for multiple ignitions and can also be re-used after re-filling.
    Type: Grant
    Filed: February 23, 2011
    Date of Patent: September 23, 2014
    Assignee: Aerospace Propulsion Products, B.V.
    Inventors: Eduardus Josephus Vermeulen, Bernd Mathias Jozef Brauers, Wilhelmina Helena Maria Welland-Veltmans
  • Patent number: 8833312
    Abstract: An external combustion engine fuel that converts the expansion force of a fluid vapor to mechanical force. In some embodiments, the external combustion engine utilizes the coolant passages of an internal combustion engine block to shroud the engine block with the heat of fuel combustion when the expanding fluid vapor is directed into the engine block.
    Type: Grant
    Filed: January 10, 2013
    Date of Patent: September 16, 2014
    Assignee: ZED Power International Corporation
    Inventor: John Berkyto
  • Publication number: 20140238038
    Abstract: A laser ignition system for a gas turbine engine includes a combustion chamber. The system comprises a laser source for generating a continuous laser beam during an ignition process of the combustion chamber; and a dynamic laser focus apparatus positioned outside of the combustion chamber and focusing the laser beam into a continuously varying focal point to generate a laser kernel moving within a spray of air/fuel mixture injected into the combustion chamber.
    Type: Application
    Filed: February 22, 2013
    Publication date: August 28, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Enzo MACCHIA, George GUGLIELMIN, Joe LANZINO, Bhawan PATEL
  • Publication number: 20140237989
    Abstract: The combustor has a laser ignitor mounted to the casing, remotely from the liner of the combustion chamber. The laser ignitor has an igniter beam path for igniting the fuel and air mixture in the combustion chamber, the igniter beam path extending at least partially across the air plenum surrounding the liner and into the combustion chamber through a corresponding beam path aperture provided in the liner.
    Type: Application
    Filed: February 26, 2013
    Publication date: August 28, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: NIGEL DAVENPORT, BHAWAN PATEL, EDUARDO HAWIE
  • Patent number: 8814562
    Abstract: An ignition system and method of igniting the ignition system includes a main catalyst section in a staged relationship with a pilot-catalyst section to stage a decomposition though the pilot-catalyst section which preheats the main catalyst section.
    Type: Grant
    Filed: June 2, 2008
    Date of Patent: August 26, 2014
    Assignee: Aerojet Rocketdyne of DE, Inc.
    Inventors: Jeff Jensen, Scott Claflin