| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390821 | With ignition device | 44 |
| 20090064657 | COMBUSTORS WITH IMPINGEMENT COOLED IGNITERS AND IGNITER TUBES FOR IMPROVED COOLING OF IGNITERS - A combustor for a gas turbine engine is provided, and includes an inner liner; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber; and an igniter tube positioning the fuel igniter relative to the combustion chamber, the igniter tube having a plurality of channels configured to direct cooling air toward the tip portion of the fuel igniter. | 03-12-2009 |
| 20090178385 | ARRANGEMENT OF A SEMICONDUCTOR-TYPE IGNITER PLUG IN A GAS TURBINE ENGINE COMBUSTION CHAMBER - The present invention relates to an arrangement comprising 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, in order to accommodate expansion along an axis perpendicular to the axis of the igniter plug. It notably comprises means for guiding air to cool the semiconductor of the igniter plug, the shell and the semiconductor defining, at their combustion-chamber end, an annular igniter plug cavity, and the shell comprising 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. | 07-16-2009 |
| 20090235635 | Igniter Assembly for a Gas Turbine - A gas turbine component ( | 09-24-2009 |
| 20100180569 | Lead Arrangement for a Combustor Unit - A lead arrangement ( | 07-22-2010 |
| 20100186368 | IGNITION/ CHEMICAL REACTION PROMOTION/ FLAME HOLDING DEVICE, SPEED-TYPE INTERNAL COMBUSTION ENGINE, AND FURNACE - An ignition and chemical reaction accelerator and flame stabilizer 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 and chemical reaction accelerator and flame stabilizer of a speed-type internal combustion engine comprises a spark plug ( | 07-29-2010 |
| 20110113747 | GUIDE FOR AN IGNITION PLUG IN A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to 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, said wall forming a body of revolution, and including 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 comprise 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. | 05-19-2011 |
| 20110146227 | APPARATUS AND ASSEMBLY FOR A SPARK IGNITER - 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. | 06-23-2011 |
| 20110225948 | APPARATUS FOR HIGH-FREQUENCY ELECTROMAGNETIC INITIATION OF A COMBUSTION PROCESS - Apparatus for providing electromagnetic radiation to a combustor during a combustion process are disclosed. An electromagnetic radiation source delivers electromagnetic radiation through a first waveguide to a second waveguide that includes an electromagnetic radiation outlet positioned to deliver electromagnetic radiation to the interior of the combustor. Electromagnetic radiation is delivered to low temperature regions of a combustor to reduce carbon monoxide (CO) and unburned hydrocarbon (UHC) emissions. In addition, the electromagnetic radiation stimulates the combustion process so that lean air-fuel mixtures and low BTU gases can be burned at lower combustion temperatures leading to reduced NOx emissions. | 09-22-2011 |
| 20120000178 | SYSTEMS INVOLVING FIBER OPTIC IGNITERS - A gas turbine engine system comprising, a gas turbine engine including a combustion area, a laser, a fuel nozzle including a cavity operative to transmit a fuel into the combustion area, and an optical fiber engaging the cavity, operative to transmit light emitted from the laser to the combustion area, wherein the light is operative to ignite the fuel in the combustion area. | 01-05-2012 |
| 20120279195 | GAS TURBINE IGNITER - An improved gas turbine igniter ( | 11-08-2012 |
| 20130025255 | ELECTRIC DISCHARGE APPARATUS - The invention relates to a gas discharge tube ( | 01-31-2013 |
| 20130255222 | GAS COMBUSTOR INSTALLED AND DETACHABLE IGNITION MODULE THEREOF - The present invention relates to a gas combustor, which includes a casing unit of the gas combustor and a detachable ignition module, the detachable ignition module is to have an igniter being modularized as a single unit, thereby being enabled to be inserted in or removed from an insertion slot preformed on a surface of the casing unit of the gas combustor, and a cathode connecting joint and a anode connecting joint of the detachable ignition module are respectively in contact with or separated from an electric conductive wire installed in the insertion slot, thereby establishing or terminating an electric connection, so the inconvenience and possible danger of replacing the igniter by the user himself is avoided. | 10-03-2013 |
| 20130263572 | ENGINE HOT SECTION VANE WITH TAPERED FLAME HOLDER SURFACE - A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end. | 10-10-2013 |
| 20140237989 | LASER-IGNITION COMBUSTOR FOR GAS TURBINE ENGINE - 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. | 08-28-2014 |
| 20140352275 | INVERTED CAP IGNITER TUBE - 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. | 12-04-2014 |
| 20140366505 | CONTINUOUS IGNITION SYSTEMS - 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. | 12-18-2014 |
| 20190145319 | GAS TURBINE COMBUSTOR | 05-16-2019 |
| 20220136696 | SURFACE IGNITER COOLING SYSTEM - An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage. | 05-05-2022 |
| 060390826 | Pilot or torch type | 8 |
| 20090165436 | Premixed, preswirled plasma-assisted pilot - A plasma enhanced pilot including a swirler mechanism is configured to be inserted into an existing blank (purge air) or liquid fuel (dual fuel) cartridge space within the centerbody of a lean, premixed land-based gas turbine combustor fuel nozzle. | 07-02-2009 |
| 20100071343 | COMPACT CYCLONE COMBUSTION TORCH IGNITER - A torch igniter and method of cooling the torch igniter includes axially flowing a first stream of gaseous oxidizer through a torch throat and vortically flowing a second stream of the gaseous oxidizer within a combustion chamber. | 03-25-2010 |
| 20110126509 | Pilot Burner of a Gas Turbine Engine, Combustor, and Gas Turbine Engine - A pilot burner of a gas turbine engine is provided. The pilot burner includes a front body with an axial expansion along a centre axis of the pilot burner, the centre axis having an axial direction towards a burning zone of the gas turbine engine. The front body includes a pilot burner face which is directed to the burning zone. A material is deposited in the front body progressing in the axial direction to form a high temperature resilient body in the axial direction of the front body and to form a high temperature resilient face of the pilot burner face. | 06-02-2011 |
| 20140305094 | GAS TURBINE COMBUSTOR - Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame. | 10-16-2014 |
| 20140305095 | GAS TURBINE COMBUSTOR - Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame. | 10-16-2014 |
| 20140360156 | Asymmetric Baseplate Cooling with Alternating Swirl Main Burners - A combustor arrangement ( | 12-11-2014 |
| 20160018109 | JET BURNER WITH COOLING DUCT IN THE BASE PLATE - A jet burner has a hot-gas side, which faces toward a combustion chamber during operation, and a cold-gas side, which faces away from a combustion chamber, including a base plate on which there are arranged multiple jet nozzles, wherein the base plate has at least one cooling duct, wherein the at least one cooling duct issues into a burner stage which comprises a pilot burner arranged on the base plate. | 01-21-2016 |
| 20220136444 | TORCH IGNITER COOLING SYSTEM - An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber. | 05-05-2022 |
| 060390827 | Spark type | 17 |
| 20100154382 | METHOD AND SYSTEMS FOR ADAPTIVE IGNITION ENERGY - A method and systems for an engine igniter excitation system includes an energy storage device, a first adaptive comparator configured to control the storage of an amount of energy in the energy storage device wherein the amount of energy is determined using at least one of an environmental parameter of the engine and a process parameter of the engine. The system also includes a second adaptive comparator communicatively coupled to the energy storage device wherein the second adaptive comparator is configured to control a rate of energy delivery to the energy storage device using at least one of an environmental parameter of the engine and a process parameter of the engine. The system also includes an igniter configured to generate a spark based on the amount of stored energy and the rate of energy delivery. | 06-24-2010 |
| 20100242432 | ADJUSTABLE IGNITER MOUNT - 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. | 09-30-2010 |
| 20100281848 | Three-point fixing arrangement of ignition electrodes of a burner - 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. | 11-11-2010 |
| 20110113748 | GUIDING AN IGNITION SPARK PLUG IN A TURBOMACHINE COMBUSTION CHAMBER - 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. | 05-19-2011 |
| 20110120077 | BURNER HAVING A PROTECTIVE ELEMENT FOR IGNITION ELECTRODES - 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. | 05-26-2011 |
| 20120110975 | IGNITER WITH INTEGRAL PRESSURE SENSING LINE - 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. | 05-10-2012 |
| 20120186222 | COMBUSTION CHAMBER OF AN AERONAUTICAL TURBINE ENGINE WITH COMBUSTION HOLES HAVING DIFFERENT CONFIGURATIONS - 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. | 07-26-2012 |
| 20120227373 | COMBUSTION CHAMBER HAVING A VENTILATED SPARK PLUG - 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. | 09-13-2012 |
| 20120255275 | GUIDING A SPARKPLUG IN A TURBINE ENGINE COMBUSTION CHAMBER - 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. | 10-11-2012 |
| 20130213004 | MULTI-ELECTRODE IGNITER FOR A GAS TURBINE ENGINE - 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. | 08-22-2013 |
| 20130213005 | SYSTEM AND METHOD FOR ZERO REACTION TIME COMBUSTION - 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. | 08-22-2013 |
| 20130327013 | SPARK PLUG FOR COMBUSTION CHAMBER OF A GAS TURBINE ENGINE - The invention relates to a spark plug for combustion chamber of a gas turbine engine comprising:
| 12-12-2013 |
| 20140345250 | IGNITER FOR A GAS TURBINE - 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. | 11-27-2014 |
| 20150020501 | AN ANNULAR COMBUSTION CHAMBER IN A TURBINE ENGINE - 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. | 01-22-2015 |
| 20150033699 | IGNITION UNIT FOR TURBOJET ENGINE - 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. | 02-05-2015 |
| 20160003150 | IGNITER TIP WITH COOLING PASSAGE - An igniter tip for a combustion system is provided. The igniter tip may include a central electrode; an insulator sleeve about the central electrode; and an outer electrode about the insulator sleeve, the outer electrode including a tubular wall having a cooling passage extending within the tubular wall, the cooling passage including an entrance opening and an exit opening to an exterior of the outer electrode. A combustion system may include the igniter tip. | 01-07-2016 |
| 20160115873 | IGNITER ASSEMBLY - An igniter assembly for a combustion system of a gas turbine engine is provided. The igniter assembly includes an igniter plug having a tip which, in use, is located at an aperture in a wall of a flame-tube of the combustion system such that the tip can provide an electrical discharge to ignite an air-fuel mixture within the flame-tube. The igniter assembly further includes a substantially annular igniter boss which locates on the wall of the flame-tube at the aperture to encircle the tip. The igniter boss has a slot formed therein at one side of the tip. An entrance of the slot receives air from outside the flame-tube and an exit of the slot delivers the air as a sheet-shaped flow over the tip. The slot is tapered such that the thickness of the slot narrows from its entrance to its exit. | 04-28-2016 |
| 060390828 | Incandescent type | 1 |
| 20090282805 | SYSTEMS INVOLVING FIBER OPTIC IGNITERS - A gas turbine engine system comprising, a gas turbine engine including a combustion area, a laser, a fuel nozzle including a cavity operative to transmit a fuel into the combustion area, and an optical fiber engaging the cavity, operative to transmit light emitted from the laser to the combustion area, wherein the light is operative to ignite the fuel in the combustion area. | 11-19-2009 |
