Spark Type Patents (Class 60/39.827)
  • Patent number: 9920729
    Abstract: Embodiments may provide a starting device for a gas internal combustion engine whereby non-combusted gas accumulating in the gas internal combustion engine and an exhaust channel is discharged before ignition startup of the gas internal combustion engine and abnormal combustion of the gas internal combustion engine is prevented so as to improve safety, breakage prevention, durability and reliability.
    Type: Grant
    Filed: January 28, 2014
    Date of Patent: March 20, 2018
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Hideki Nishio, Michiyasu Ishida, Hirotoshi Kitagawa
  • Patent number: 9856031
    Abstract: An aircraft with a turbofan engine including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supply to the ignition plug, and at least a part of the igniter cable is passed through an inside of the pylon.
    Type: Grant
    Filed: February 5, 2015
    Date of Patent: January 2, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Jingo Tateiwa
  • Patent number: 9739204
    Abstract: A gas turbine igniter includes an igniter rod disposed within a guide tube configured for travel between a hot-end region and a cold-end region and a cap connected to the guide tube, the cap defining an access passageway for the igniter rod. An attachment structure is provided for reducing the moment loading at the cold end of the igniter rod. The attachment structure has threaded outer surface configured to engage in a threaded connection with a threaded inner surface of the cap in an end portion of the cap that is proximate to the cold-end region, whereby the attachment structure is attachable to the end portion of the cap via the threaded connection. An inner surface of the attachment structure forms a guide surface for the igniter rod, at a reduced radial clearance with the igniter rod in comparison to the cap, proximate to the cold-end region.
    Type: Grant
    Filed: May 9, 2013
    Date of Patent: August 22, 2017
    Assignee: Siemens Energy, Inc.
    Inventor: Derek A. Bird
  • Patent number: 9562692
    Abstract: A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body.
    Type: Grant
    Filed: January 27, 2014
    Date of Patent: February 7, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Steven Williams, Timothy A. Fox, Reinhard Schilp
  • Patent number: 9273867
    Abstract: An integrated retractable burner ignition system including a burner having an outlet face and a flow passage including a front end substantially coincident with the outlet face of the burner and a gas inlet positioned rearward from the front end of the flow passage, an igniter including a high voltage electrode surrounded by an insulator and extending beyond the insulator to form a tip end of the igniter, the igniter being mounted slidably within the flow passage, an actuator connected to a rear portion of the igniter and configured to advance and retract the igniter within the flow passage, and a slidable seal between the igniter and the flow passage, the seal being positioned rearward of the gas inlet of the flow passage and frontward of the rear portion of the igniter.
    Type: Grant
    Filed: February 4, 2013
    Date of Patent: March 1, 2016
    Assignee: AIR PRODUCTS AND CHEMICALS, INC.
    Inventors: Michael David Buzinski, Shailesh Pradeep Gangoli, William Otto Litrenta, Reed Jacob Hendershot, Larry Saul Zelson
  • Patent number: 9080771
    Abstract: A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.
    Type: Grant
    Filed: November 15, 2010
    Date of Patent: July 14, 2015
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Guillaume Sevi
  • Patent number: 9046270
    Abstract: The present invention relates to a flameholder (1) for holding a flame (84) comprising a flow of combusting fluid. The flameholder (1) comprises an inlet (32) and an outlet (34) which defines a flow path between them. A magnetic-field generator (10, 20) is arranged to generate a magnetic field (40) across the flow path such that in use the fluid flows in the flow path through the magnetic field (40). As the fluid flows through the magnetic field an electric current is induced in the fluid. This results in a force (86) being generated on the fluid which opposes the flow direction (82). This force acts to hold the flame in place. If the flow path is in the form of a closed loop, in a plane perpendicular to the flow direction (82), then the current (50) induced in the fluid can flow in a closed loop entirely within the fluid.
    Type: Grant
    Filed: July 12, 2011
    Date of Patent: June 2, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Simon A. Weeks, Christopher G. Bright
  • 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
  • Publication number: 20150047361
    Abstract: A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip.
    Type: Application
    Filed: January 27, 2014
    Publication date: February 19, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Steven Williams, Timothy A. Fox, Reinhard Schilp
  • Publication number: 20150033699
    Abstract: An ignition unit for a turbojet engine, including: an electrical power supply, a single control channel to receive a control signal from a computer, a main sparkplug ignition channel to energize at least one main sparkplug of a main combustion chamber, and an afterburner sparkplug ignition channel to energize at least one afterburner sparkplug of an afterburner chamber. The ignition unit is configured, in response to pulsed controls on the single control channel, to selectively activate the main sparkplug ignition channel or the afterburner sparkplug ignition channel.
    Type: Application
    Filed: March 22, 2013
    Publication date: February 5, 2015
    Applicant: SNECMA
    Inventors: Christian Schaeffer, David Gino Stifanic, Bertrand Boedot
  • Publication number: 20150020501
    Abstract: An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.
    Type: Application
    Filed: October 22, 2012
    Publication date: January 22, 2015
    Applicant: SNECMA
    Inventors: Sebastien Alain Christophe Bourgois, Denis Jean Maurice Sandelis
  • Publication number: 20140345250
    Abstract: A gas turbine igniter includes an igniter rod disposed within a guide tube configured for travel between a hot-end region and a cold-end region and a cap connected to the guide tube, the cap defining an access passageway for the igniter rod. An attachment structure is provided for reducing the moment loading at the cold end of the igniter rod. The attachment structure has threaded outer surface configured to engage in a threaded connection with a threaded inner surface of the cap in an end portion of the cap that is proximate to the cold-end region, whereby the attachment structure is attachable to the end portion of the cap via the threaded connection. An inner surface of the attachment structure forms a guide surface for the igniter rod, at a reduced radial clearance with the igniter rod in comparison to the cap, proximate to the cold-end region.
    Type: Application
    Filed: May 9, 2013
    Publication date: November 27, 2014
    Inventor: DEREK A. BIRD
  • 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
  • Publication number: 20140290259
    Abstract: A combustion systems and components for rotary ramjet engines. An injection system, optionally stratified for ease of engine startup, provides an air and fuel mixture to a combustion chamber. An ignition system ignites the mixture. A flameholding system may be positioned for communication with the combustion chamber to force an ignited flow of the air and fuel mixture toward a center of rotation within the ramjet engine. The ramjet engine may have a diverging stator for improved exhaust efficiency. The ignition may take place in the engine air intake. Alternatively, the ignition may take place within the combustion chamber using a dual-hub electrically charged system. An impulse turbine may use recirculation of injected fuel to cool a rim-rotor and/or to reduce windage on the rim-rotor. A sealing system may reduce gas leaks from a fuel conduit into the engine air intake.
    Type: Application
    Filed: May 25, 2012
    Publication date: October 2, 2014
    Applicant: SOCPRA SCIENCES ET GENIE, S.E.C.
    Inventors: Jean-Sébastien Plante, Mathieu Picard, David Rarncourt
  • Patent number: 8763401
    Abstract: There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.
    Type: Grant
    Filed: May 30, 2011
    Date of Patent: July 1, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Enzo Macchia, Oleg Morenko, George Guglielmin
  • Patent number: 8733078
    Abstract: An igniter device for a combustor system includes an igniter housing and a pressure sense passage. The igniter housing surrounds an electrode and an insulating body. The igniter has a tip to be positioned within a chamber for combustion. The pressure sense passage is attached to an exterior surface of the igniter housing. The pressure sense passage is configured to direct fluid to a pressure sensor.
    Type: Grant
    Filed: November 10, 2010
    Date of Patent: May 27, 2014
    Assignee: United Technologies Corporation
    Inventor: Hannes A. Alholm
  • Patent number: 8713908
    Abstract: An arrangement for a combustion chamber the arrangement comprising a combustion chamber, an injector for injecting fuel into the combustion chamber and an igniter for supplying a spark for igniting fuel so injected, wherein the injector has a passage through which air is supplied to the combustion chamber in use, the igniter being positioned upstream of the combustion chamber such that a spark generated by the igniter is conveyed along the passage by the injector air.
    Type: Grant
    Filed: March 22, 2012
    Date of Patent: May 6, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Stephen C. Harding
  • Patent number: 8653693
    Abstract: An integrated exciter-igniter architecture is disclosed that integrates compact, direct-mounted exciter electronics with an aerospace designed igniter to reduce overall ignition system complexity. The integrated exciter-igniter unit hermetically seals exciter electronics within a stainless steel enclosure or housing. The stainless enclosure enables the exciter electronics to remain near atmospheric pressure while the unit is exposed to vacuum conditions. The exciter electronics include a DC-DC converter, timing circuitry, custom-designed PCBs, a custom-designed main power transformer, and a high voltage ignition coil. All of which are packaged together in the stainless steel enclosure. The integrated exciter-igniter unit allows for efficient energy delivery to the spark gap and eliminates the need for a high voltage cable to distribute the high voltage, high energy pulses.
    Type: Grant
    Filed: January 27, 2011
    Date of Patent: February 18, 2014
    Assignee: Alphaport, Inc.
    Inventors: Michael Vincent Aulisio, Greg Scott Tollis, Elmer L. Griebeler, Neil D. Rowe
  • Publication number: 20130327013
    Abstract: The invention relates to a spark plug for combustion chamber of a gas turbine engine comprising: an external body (1) forming ground electrode, intended to be received mainly in a bypass of the combustion chamber, an internal central electrode (2), an interposed insulator (3) with clearance between the external body (1) and the internal electrode (2), said spark plug terminating in a nose forming portion (5) intended for its part to be received in the flame tube of the chamber of the combustion chamber, a semi-conductor element being interposed between the central electrode and the ground electrode at the level of said nose forming portion, wherein the external body (1) comprises at least one cooling air inlet (6) which communicates inside the spark plug with at least one outlet (8, 9, 10) arranged at the level of the nose forming portion.
    Type: Application
    Filed: April 12, 2013
    Publication date: December 12, 2013
    Applicant: SNECMA
    Inventors: Francois LEGLAYE, Jean-Francois CABRE, David Gino STIFANIC
  • Patent number: 8590285
    Abstract: A burner having two ignition electrodes and a bracket is provided. The bracket is arranged on the outer surface of the burner and the ignition electrodes are held, at in each case three points of their periphery, in a fixed position using the bracket. A gas turbine with the burner is also provided.
    Type: Grant
    Filed: June 30, 2008
    Date of Patent: November 26, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventors: Christian Hohmann, Andre Kluge, Roland Liebe, Elmar Pfeiffer
  • Patent number: 8534041
    Abstract: An apparatus and assembly for an igniter is provided. The igniter includes a shell comprising a base, a tip surface, and a sidewall extending therebetween wherein the sidewall surrounds a cavity within the shell. The igniter also includes a shell bore extending from the tip surface to the cavity and a pin embedded into the tip surface extending substantially tangentially with respect to the bore.
    Type: Grant
    Filed: December 23, 2009
    Date of Patent: September 17, 2013
    Assignee: Unison Industries, LLC
    Inventors: Brendon Francis Mee, Randal Parker Bold
  • Publication number: 20130213005
    Abstract: A system and method for zero reaction time combustion is provided where a gaseous or dispersive fuel-oxidant mixture is supplied to a fill point of a tube having a fill point and an open end. An igniter placed at an ignition point in the tube continuously ignites the gaseous or dispersive fuel-oxidant mixture while the gaseous or dispersive fuel-oxidant mixture is flowing through the tube thereby continuously producing zero reaction time combustion at that ignition point that produces exhaust and a continuous pressure. The exhaust travels from the ignition point to the open end of the tube.
    Type: Application
    Filed: February 8, 2013
    Publication date: August 22, 2013
    Applicant: SOUNDBLAST TECHNOLOGIES, LLC
    Inventor: Soundblast Technologies, LLC
  • Publication number: 20130213004
    Abstract: An ignition system for a combustor of a gas turbine engine is disclosed. The ignition system may include multiple igniters to reduce the likelihood of system failure. In at least one embodiment, the ignition system may be formed from a first igniter formed from an outer electrode containing at least one central electrode at a distal end of the outer electrode and may include a second igniter. The second igniter may be formed from a central electrode positioned within the outer electrode forming the first igniter. During operation, the igniters may spark to ignite the fuel mixture within the combustor.
    Type: Application
    Filed: February 22, 2012
    Publication date: August 22, 2013
    Inventors: Shervin Rodd, Ryan Kelbey, Adam M. Foust, Jim Causey
  • Patent number: 8505275
    Abstract: A turbomachine including a combustion chamber provided with systems for injecting fuel into the chamber, and with at least one spark plug is disclosed. The injection system located as close as possible to the spark plug is configured in order to produce a pool of fuel having an angle of opening of a greater value than that of the pools produced by the other injection systems, and having a flow of fuel greater than that of the other injection systems.
    Type: Grant
    Filed: January 14, 2010
    Date of Patent: August 13, 2013
    Assignee: Snecma
    Inventors: Dominique Maurice Jacques Lains, Denis Jean Maurice Sandelis
  • Patent number: 8505303
    Abstract: The present invention discloses a combustor system and method of measuring impurities in the combustion system. The combustion system includes an up-stream fuel injection point; a down-stream turbine combustor; a flame zone in the turbine combustor comprising a plurality of axial sub-zones; an optical port assembly configured to obtain a non-axial, direct, optical view of at least one of the plurality of axial sub-zones, and an impurity detection system in optical communication with the optical port assembly.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: August 13, 2013
    Assignee: General Electric Company
    Inventors: Peter Micah Sandvik, Richard Dale Slates, Alexey Vasily Vert, Samer Aljabari
  • Publication number: 20130125558
    Abstract: A method of igniting a turbine engine using a spark plug including a first electrode, a second electrode, and a semiconductor body between the first electrode and the second electrode, the semiconductor body having an exposed surface, the ignition method including: generating a spark adjacent to the exposed surface by applying a voltage difference greater than a first predetermined threshold between the first electrode and the second electrode; and prior to generating a spark, a preheating applying a voltage difference less than a second predetermined threshold between the first electrode and the second electrode, the second predetermined threshold being less than the first predetermined threshold.
    Type: Application
    Filed: May 25, 2011
    Publication date: May 23, 2013
    Applicant: Snecma
    Inventors: Luc Henri Chatenet, Christian Schaeffer, David Stifanic
  • Publication number: 20130111914
    Abstract: An aircraft ignition system having a power circuit, a control circuit, and a discharge circuit and coupled to the spark plugs of an aircraft engine. The power circuit may include two independent power sources; e.g., alternator power (such as a permanent magnet alternator) and power from aircraft or DC power bus. The control circuit may control one or more aspects of the discharge circuit, e.g., the ignition timing. And the discharge circuit may trigger a capacitive discharge ignition event to the spark plugs.
    Type: Application
    Filed: April 27, 2012
    Publication date: May 9, 2013
    Applicant: CHAMPION AEROSPACE LLC
    Inventor: Steve J. Kempinski
  • Publication number: 20130047577
    Abstract: An ignition circuit is provided and may include a dc-dc converter having a positive terminal and a negative terminal, an igniter plug having a first terminal and a second terminal, a first capacitor coupled to the positive terminal, a first diode coupled between the first capacitor and the negative terminal, a switching circuit coupled between the positive terminal, and the negative terminal, a second capacitor, a transformer having a primary and a secondary winding, the primary winding coupled between the negative terminal and the second capacitor and the secondary winding coupled between the negative terminal and the first terminal of igniter plug, and a second diode coupled between the first capacitor and the second terminal, wherein the second capacitor is coupled between the primary winding and the second diode, and wherein the first terminal is coupled to the secondary winding and the second terminal is connected to a ground.
    Type: Application
    Filed: August 29, 2011
    Publication date: February 28, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Deepak Mahajan, Renukaprasad N.
  • Publication number: 20130029236
    Abstract: A device used to provide hot exhaust gases for driving a turbine. The device includes a burner, the combustion zone of which is directly mounted on or integrated into the gas inlet (turbine housing) of the turbine. The burner is supplied with at least one combustible gas or gas mixture. The combustion zone includes a porous material with a large specific surface area.
    Type: Application
    Filed: December 4, 2010
    Publication date: January 31, 2013
    Applicant: Daimler AG
    Inventors: Holger Stark, Ulf-Michael Mex, Gerhard Konrad, Benjamin Steinhauser, Gert Hinsenkamp
  • Patent number: 8327616
    Abstract: A gas turbine burner with an igniter and an ignition electrode for installation in a main burner of a gas turbine is disclosed. The ignition electrode is protected from damage by a protective element.
    Type: Grant
    Filed: August 14, 2007
    Date of Patent: December 11, 2012
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Böttcher, Andre Kluge, Claus Krusch, Elmar Pfeiffer, Sabine Tüschen
  • Publication number: 20120255275
    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: Application
    Filed: December 3, 2010
    Publication date: October 11, 2012
    Applicant: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Nicolas Christian Raymond Leblond, Guillaume Sevi, Denis Jean Maurice Sandelis, Christophe Pieussergues
  • Publication number: 20120227373
    Abstract: A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.
    Type: Application
    Filed: November 15, 2010
    Publication date: September 13, 2012
    Applicant: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Guillaume Sevi
  • Patent number: 8230672
    Abstract: High performance propellants flow through specialized mechanical hardware that allows for effective and safe thermal decomposition and/or combustion of the propellants. By integrating a sintered metal component between a propellant feed source and the combustion chamber, an effective and reliable fuel injector head may be implemented. Additionally the fuel injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.
    Type: Grant
    Filed: December 4, 2007
    Date of Patent: July 31, 2012
    Assignee: Firestar Engineering, LLC
    Inventors: Gregory Stuart Mungas, David James Fisher, Christopher Mungas
  • Patent number: 8230673
    Abstract: Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media element between a propellant feed source and the combustion chamber, an effective and reliable propellant injector head may be implemented that is capable of withstanding transient combustion and detonation waves that commonly occur during an ignition event. The micro-fluidic porous media element is of specified porosity or porosity gradient selected to be appropriate for a given propellant. Additionally the propellant injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.
    Type: Grant
    Filed: November 5, 2009
    Date of Patent: July 31, 2012
    Assignee: Firestar Engineering, LLC
    Inventors: Gregory S. Mungas, David J. Fisher, Christopher Mungas
  • Publication number: 20120186222
    Abstract: A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.
    Type: Application
    Filed: September 21, 2010
    Publication date: July 26, 2012
    Applicant: SNECMA
    Inventors: Patrice Andre Commaret, Thomas Olivier Marie Noel
  • Patent number: 8181440
    Abstract: An igniter plug arrangement is disclosed. The arrangement includes an igniter plug of the semiconductor in shell type, a duct secured to a combustion chamber of a gas turbine engine, a floating sleeve via which the igniter plug is mounted in the duct, and a system for guiding air to cool the semiconductor of the igniter plug. The shell and the semiconductor define, at their combustion-chamber end, an annular igniter plug cavity. The shell includes orifices in the region of the igniter plug annular cavity that communicate with the annular cavity of the sleeve and orifices on its planar surface.
    Type: Grant
    Filed: January 14, 2009
    Date of Patent: May 22, 2012
    Assignee: SNECMA
    Inventor: Denis Jean Maurice Sandelis
  • Publication number: 20120110975
    Abstract: An igniter device for a combustor system includes an igniter housing and a pressure sense passage. The igniter housing surrounds an electrode and an insulating body. The igniter has a tip to be positioned within a chamber for combustion. The pressure sense passage is attached to an exterior surface of the igniter housing. The pressure sense passage is configured to direct fluid to a pressure sensor.
    Type: Application
    Filed: November 10, 2010
    Publication date: May 10, 2012
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Hannes A. Alholm
  • Patent number: 8171719
    Abstract: An igniter assembly (10) of a gas turbine (12) is presented, including an igniter (14) disposed within an igniter housing (16). The igniter is extendable from the igniter housing through an opening (18) in a combustion liner (19) to an extended position, and is retractable from the extended position back through the opening to a retracted position (22). The igniter assembly further includes a compressible assembly (24) disposed between a base (26) of the igniter housing and the combustion liner to form a sealed interface (15) with a perimeter (28) of the opening (18). The compressible assembly is configured to restrict an air flow from passing between the igniter housing base and the perimeter of the opening. The compressible assembly is variable in length to accommodate a respective variation in a separation between the igniter housing base (26) and the opening (18).
    Type: Grant
    Filed: March 21, 2008
    Date of Patent: May 8, 2012
    Assignee: Siemens Energy, Inc.
    Inventor: William R. Ryan
  • Patent number: 8122703
    Abstract: A bi-propellant injector includes first and second injector elements and a spark exciter assembly. The first injector element has a conductive layer electrically connected to the spark exciter assembly and a nonconductive layer disposed on an exterior portion of the conductive layer. The second injector element comprises a conductive material and has an opening therethrough in fluid communication with a combustion chamber. An end of the first injector element is positioned at or near the opening in the second injector element. The spark exciter assembly can generate an electrical arc between the conductive layer of the first injector element and the second injector element.
    Type: Grant
    Filed: April 28, 2006
    Date of Patent: February 28, 2012
    Assignee: United Technologies Corporation
    Inventor: Steven C. Fisher
  • Patent number: 8099963
    Abstract: The present invention relates to a device for mounting an igniter plug in a combustion chamber of a gas turbine engine contained in a casing, in which the combustion chamber has an axis YY, the mounting device comprising a hollow shaft, of axis XX, a floating igniter plug sleeve absorbing expansion along an axis perpendicular to the axis XX of the hollow shaft. The device is one which further comprises a hollow shaft sleeve such that the igniter plug sleeve is housed in the hollow shaft sleeve, and means of inclining said hollow shaft sleeve relative to the axis XX. Inclining the hollow shaft sleeve allows the chamber to be inclined relative to the axis XX.
    Type: Grant
    Filed: February 11, 2009
    Date of Patent: January 24, 2012
    Assignee: Snecma
    Inventors: Christophe Pieussergues, Denis Jean Maurice Sandelis
  • Patent number: 8046987
    Abstract: An air cooled core mounted ignition system for gas turbine engine applications is provided. The ignition system includes an ignition exciter component directly mechanically and electrically connected to an igniter component. The housing member of the exciter component includes an air plenum configured to receive bleed air from the engine fan or compressor sections of the turbine engine, or other source. The bleed air provides a relatively low temperature air source for the purpose of cooling the exciter. As such, the exciter component can be directly secured to the igniter, thereby eliminating the need for an ignition lead.
    Type: Grant
    Filed: September 3, 2008
    Date of Patent: November 1, 2011
    Assignee: Woodard, Inc.
    Inventors: Theodore Steven Wilmot, Ryan Gilbert Kelbey
  • Patent number: 8015813
    Abstract: A fuel injector for injecting fuel into a turbomachine combustion chamber, the injector presenting an injector nose for connection to an injection system fastened to the end wall of said combustion chamber, the injector nose comprising: a first channel for passing a flow of an air/fuel pre-mixture towards the combustion chamber, the first channel opening out into the center of the injector nose via an outlet opening for the air/fuel pre-mixture; an electrical insulator surrounding said outlet opening for the air/fuel pre-mixture; a plasma generator system disposed inside said electrical insulation and downstream from said outlet opening for the air/fuel pre-mixture in order to control ignition and combustion of the air/fuel pre-mixture; a second channel for passing a flow of fuel towards the combustion chamber, the second channel opening out outside said electrical insulation; and a third channel for passing a flow of fuel towards the combustion chamber, this third channel opening out outside the second ch
    Type: Grant
    Filed: July 29, 2008
    Date of Patent: September 13, 2011
    Assignee: SNECMA
    Inventors: Michel Pierre Cazalens, Thomas Olivier Marie Noel
  • Publication number: 20110120077
    Abstract: A gas turbine burner with an igniter and an ignition electrode for installation in a main burner of a gas turbine is disclosed. The ignition electrode is protected from damage by a protective element.
    Type: Application
    Filed: August 14, 2007
    Publication date: May 26, 2011
    Inventors: Andreas Böttcher, Andre Kluge, Claus Krusch, Elmar Pfeiffer, Sabine Tüschen
  • Patent number: 7946119
    Abstract: An arrangement for sealing an opening formed in a wall for receiving a member. The arrangement comprises a sealing member with a passage, and the sealing member is moveably mounted on the wall adjacent to the opening such that the sealing member passage is substantially co-axial with the opening in the wall. Biasing means for biasing the sealing member towards the wall are also provided.
    Type: Grant
    Filed: October 24, 2006
    Date of Patent: May 24, 2011
    Assignee: Rolls-Royce PLC
    Inventor: Alan Philip Geary
  • Publication number: 20110113748
    Abstract: The invention relates to a turbomachine combustion chamber including at least one ignition spark plug carried by an outer casing and extending in guide means carried by a wall of the chamber, the wall forming a body of revolution, the guide means comprising a tubular guide having the spark 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. In order to reduce wear of the spark plug in operation, the spark plug is mounted by being fastened in a sheath, the tubular guide being slidably mounted around the sheath.
    Type: Application
    Filed: November 15, 2010
    Publication date: May 19, 2011
    Applicant: SNECMA
    Inventors: Dominique Maurice Jacques LAINS, Nicolas Christian Raymond Leblond, Christophe Pieussergues
  • Patent number: 7833011
    Abstract: A method of igniting and monitoring a high speed burner with which a fuel/oxygen-mixture exits at high velocity from a burner head, wherein the length of the flame is governed by the exit velocity of the mixture. The invention is characterized by placing an electrically conductive pipe in and concentrical with the burner channel for the fuel mixture, by causing a first end of the pipe to terminate close to the fuel mixture outlet of the burner head, by electrically isolating the pipe and by causing the detection of light of the group ultraviolet light, visible light and/or infrared light to be detected at the other end of the pipe, and by causing a spark to be generated between the first end of the pipe and the surrounding burner head by application of a voltage, in igniting the burner. A burner is also disclosed.
    Type: Grant
    Filed: October 11, 2005
    Date of Patent: November 16, 2010
    Assignee: Sandvik Intellectual Property AB
    Inventors: Bo Jönsson, Kari Korhonen, Pauli Mäenpää, Thomas Lewin
  • Publication number: 20100281848
    Abstract: A burner having two ignition electrodes and a bracket is provided. The bracket is arranged on the outer surface of the burner and the ignition electrodes are held, at in each case three points of their periphery, in a fixed position using the bracket. A gas turbine with the burner is also provided.
    Type: Application
    Filed: June 30, 2008
    Publication date: November 11, 2010
    Inventors: Dr. Christian Hohmann, Andre Kluge, Dr. Roland Liebe, Elmar Pfeiffer
  • Publication number: 20100242432
    Abstract: An ignition assembly for providing increased movement of an igniter within a combustor is provided. The ignition assembly includes a base assembly having a first base plate, a second base plate, and a positioning plate, where the positioning plate contains an igniter and is capable of adjusting in an axial and/or circumferential direction relative to the combustor.
    Type: Application
    Filed: March 24, 2009
    Publication date: September 30, 2010
    Applicant: ALSTOM TECHNOLOGIES LTD. LLC
    Inventor: Daniel J. Sullivan
  • Publication number: 20100229559
    Abstract: Turbomachine, comprising a combustion chamber provided with systems (132, 132?) for injecting fuel into the chamber, and with at least one spark plug (144), the injection system (132) located as close as possible to the spark plug being configured in order to produce a pool (166) of fuel having an angle of opening (?) of a greater value than that (?) of the pools (166?) produced by the other injection systems (132?), and having a flow of fuel greater than that of the other injection systems (132?).
    Type: Application
    Filed: January 14, 2010
    Publication date: September 16, 2010
    Applicant: SNECMA
    Inventors: Dominique Maurice Jacques LAINS, Denis Jean Maurice Sandelis