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.

Stosswellenbrenner und Verwendung eines solchen

Laser ignition system

In a laser ignition system (2) for igniting fuel sprayed into a combustion chamber, comprising a laser beam generating source (4) coupled to an optical fiber (8) to transmit the beam into the chamber, the coupling system includes a coupling lens (8) for focusing the beam at a point upstream of the fiber, a source-fiber connector (17) and a device (16) for keeping the fiber inlet section straight, downstream of the connector and extending a specific distance along the fiber.

LASER IGNITION SYSTEM

Shock wave burners

ADVANCED OPTICS AND OPTICAL ACCESS FOR LASER IGNITION SYSTEMS FOR GAS TURBINES INCLUDING AIRCRAFT ENGINES

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.

Equal space combustion chamber

SUPPLEMENTARY LASER FIRING FOR COMBUSTION STABILITY

The present invention relates to a combustion system for a gas turbine. The combustion system comprises a combustion chamber (100) having an end section (101) and a pre-combustion section (102) extending from the end section (101) along a centre axis (103) of the combustion chamber (100), a swirler device (110), an optional pilot burner device (120) and a light emitting arrangement (130). The swirler device (110) is mounted to the pre-combustion section (102) such that a main fuel (111) is injectable by or through the swirler device (110) into an inner volume (104) of the pre- combustion section (102). The main flame (108) using the main fuel (111) is producible inside the inner volume (104). The optional pilot burner device (120) is mounted to the end section (101) of the combustion chamber (100) such that a pilot fuel (121) is injectable by or through the pilot burner device (120) into the inner volume (104) of the pre-combustion section (102), wherein a pilot flame (122) using the pilot ...

GAS TURBINE VARIABLE FOCUS LASER IGNITION

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.

Advanced optics and optical access for laser ignition systems for combustion engines

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.

Laser initiated non-linear fuel droplet ignition

Method and apparatus for igniting an air/fuel spray (26) comprised of fuel droplets. The apparatus includes a coherent optical source (12) for introducing at least one pulse of coherent radiation into the air/fuel spray. The pulse generates free electrons and initiates a development of a plasma within the air/fuel spray. The coherent source maintains the pulse of coherent radiation and pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy and before ignition of the air/fuel spray. The non-linear ignition system of the invention employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends from and exists outside of a fuel droplet. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time an avalanche process occurs that creates a high density of free electrons and ions which results in the formation of a plasma.

Laser ignition system, e.g. for industrial or aeronautical turbines, comprises laser beam source coupled to optical fiber for transmission to combustion chamber via lens, connector and straightening device

L'invention concerne un système d'allumage laser (2) d'un carburant pulvérisé dans une chambre de combustion, le système comportant une source laser (4) adaptée pour générer un faisceau laser, une fibre optique (8) propre à transmettre le faisceau laser généré dans la chambre de combustion et des moyens de couplage (12,16,17) de la source laser (4) à la fibre optique (8). Les moyens de couplage (12, 16, 17) comprennent une lentille de focalisation propre à focaliser le faisceau laser en un point focal situé en amont de la fibre optique (8), un connecteur (17) de raccordement de la source laser (4) à la fibre optique (8), et des moyens (16) de maintien rectilignes d'un tronçon d'entrée de la fibre optique (8) disposés en aval du connecteur (17) et s'étendant sur une distance prédéfinie de la fibre optique (8). Application aux turbomachines industrielles et aéronautiques.

LASER IGNITION SYSTEM

ADVANCED LASER IGNITION SYSTEMS FOR GAS TURBINES INCLUDING AIRCRAFT ENGINES

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system comprises at least one laser light source configured to generate a laser beam and an optical beam guidance component. The optical beam guidance component is configured to transmit the laser beam to irradiate on an oxygenated fuel mixture supplied into the combustion chamber at a region of highest ignitability to generate a combustor flame in a flame region. The system further includes an integrated control diagnostic component configured to detect at least a portion of a light emission and operable to control one or more combustion parameters based in part on the detected light emission. The system further includes additional enhanced ignition control configurations. A method for igniting a fuel mixture in an internal combustion engine is also presented.

SUPPLEMENTARY LASER FIRING FOR COMBUSTION STABILITY

The present invention relates to a combustion system for a gas turbine. The combustion system comprises a combustion chamber (100) having an end section (101) and a pre-combustion section (102) extending from the end section (101) along a centre axis (103) of the combustion chamber (100), a swirler device (110), an optional pilot burner device (120) and a light emitting arrangement (130). The swirler device (110) is mounted to the pre-combustion section (102) such that a main fuel (111) is injectable by or through the swirler device (110) into an inner volume (104) of the pre- combustion section (102). The main flame (108) using the main fuel (111) is producible inside the inner volume (104). The optional pilot burner device (120) is mounted to the end section (101) of the combustion chamber (100) such that a pilot fuel (121) is injectable by or through the pilot burner device (120) into the inner volume (104) of the pre-combustion section (102), wherein a pilot flame (122) using the pilot fuel (121) is producible inside the inner volume (104) for stabilizing the main flame (108). The light emitting arrangement (130) emits an electromagnetic radiation (131) into the inner volume (104), wherein the light emitting arrangement (130) is arranged to the combustion chamber (100) such that an energy input to the pilot flame (122) and/or the main flame (108) is generatable by the electromagnetic radiation (131) for stabilizing the pilot flame (122) and/or the main flame (108), particularly to reduce the fuel required by the pilot flame and hence the emissions. The light emitting arrangement could also be used to replace the function of the pilot flame and be used to stabilise the main flame instead of using a pilot flame.

Laser ignition system, e.g. for industrial or aeronautical turbines, comprises laser beam source coupled to optical fiber for transmission to combustion chamber via lens, connector and straightening device

L'invention concerne un système d'allumage laser (2) d'un carburant pulvérisé dans une chambre de combustion, le système comportant une source laser (4) adaptée pour générer un faisceau laser, une fibre optique (8) propre à transmettre le faisceau laser généré dans la chambre de combustion et des moyens de couplage (12, 16, 17) de la source laser (4) à la fibre optique (8). Les moyens de couplage (12, 16, 17) comprennent une lentille de focalisation propre à focaliser le faisceau laser en un point focal situé en amont de la fibre optique (8), un connecteur (17) de raccordement de la source laser (4) à la fibre optique (8), et des moyens (16) de maintien rectilignes d'un tronçon d'entrée de la fibre optique (8) disposés en aval du connecteur (17) et s'étendant sur une distance prédéfinie de la fibre optique (8). Application aux turbomachines industrielles et aéronautiques.

Ignition methods and apparatus for combustors

Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main fuel nozzle is provided which includes a plurality of electrostatic fuel nozzles disposed about a centrally located igniter. In one embodiment, the igniter is a laser igniter.

Method for initiating an exothermic chemical reaction, bypassing the heating of the mass of the reactants to the reaction temperature

Method for initiating an exothermic chemical reaction, bypassing the heating of the mass of the reaction partners to the reaction temperature, by passing the mixture (6) of substances to be reacted over or through a catalyst bed (3) which is situated in the reaction space (2) and the surface of which is impinged by a laser beam (4) transmitted through an IR-transparent window (5). Accelerated reaction of organic substances at comparatively low mean temperatures. Flameless combustion of fuels without preheating (internal combustion engines). Remote ignition. Controlling ignition processes without problems of supplying and removing heat. ...

ADVANCED LASER IGNITION SYSTEMS FOR GAS TURBINES INCLUDING AIRCRAFT ENGINES

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system comprises at least one laser light source configured to generate a laser beam and an optical beam guidance component. The optical beam guidance component is configured to transmit the laser beam to irradiate on an oxygenated fuel mixture supplied into the combustion chamber at a region of highest ignitability to generate a combustor flame in a flame region. The system further includes an integrated control diagnostic component configured to detect at least a portion of a light emission and operable to control one or more combustion parameters based in part on the detected light emission. The system further includes additional enhanced ignition control configurations. A method for igniting a fuel mixture in an internal combustion engine is also presented.

IGNITION METHOD AND APPARATUS USING BROADBAND LASER ENERGY

An ignition apparatus for a combustor includes a broadband laser energy source that emits laser energy into the combustor, the broadband laser energy having at least two fundamental wavelengths, to produce a plasma that ignites a combustible mixture therein. In one embodiment, laser energy in the ultraviolet and infrared regions are emitted into the combustor. Intensity and time characteristics for the laser energy including fluence, pulse duration, repetition rate, peak intensity and average intensity can also be controlled for one or more of the fundamental wavelengths to further enhance the ignition and combustion processes.

LASER IGNITION SYSTEM AND METHOD FOR INTERNAL COMBUSTION ENGINE

Einrichtung und Verfahren zum Zünden einer Brennkammeranordnung

Eine Düse (30) enthält einen zentralen Grundkörper (32), der eine axiale Mittellinie (38) definiert. Ein Mantel (34) umgibt wenigstens einen Abschnitt des zentralen Grundkörpers (32), um zwischen dem zentralen Grundkörper (32) und dem Mantel (34) einen ringförmigen Durchlasskanal (40) zu bilden. Ein Sammelraum (44, 46) ist im Inneren des zentralen Grundkörpers (32) und im Wesentlichen parallel zu der axialen Mittellinie (38) angeordnet, und eine Zündvorrichtung (52) ist im Inneren des zentralen Grundkörpers (32) und im Wesentlichen benachbart zu dem Sammelraum (44, 46) angeordnet. Ein Verfahren zum Zünden einer Brennkammeranordnung (10) beinhaltet die Schritte: Leiten eines Brennstoffs durch einen zentralen Grundkörper (32), der axial fluchtend in einer Düse (30) ausgerichtet ist; und Leiten eines Arbeitsfluids durch einen ringförmigen Durchlasskanal (40), wobei der ringförmige Durchlasskanal (40) im Wesentlichen parallel zu und radial außerhalb des zentralen Grundkörpers (32) angeordnet ...

Shock wave burners

... 1,111,080. Lasers. SIEMENS-SCHUCKERTWERKE A.G. 23 Sept., 1966 [25 Sept., 1965], No. 42701/66. Heading H1C. [Also in Divisions E1 and F4] In a shock wave burner comprising a combustion chamber 1 with a fuel injection device 3, controlled to inject a combustible mixture periodically into the chamber 1, at a predetermined injection frequency a laser ignition device 2, comprising a ruby crystal 13, a flash-lamp 14, capacitor and ignition coil 15, capacitor battery and power supply 16 and lens 17 is controlled by a control unit 4 to operate periodically at the injection rate so that constant volume combustions of the injected mixture are produced periodically in the chamber at the injection frequency. Applications of the burner include aircraft driven on the reaction principle and MHD generators.

IGNITION DEVICE ESPECIALLY FOR AN INTERNAL COMBUSTION ENGINE, AND METHOD FOR THE PRODUCTION THEREOF

The invention relates to an ignition device (27), in particular for an internal combustion engine of a motor vehicle, comprising a laser device (26) for generating laser pulses (24), and an optical fiber device (280) that is at least optically connected to the laser device (26) to apply pumping light (60) to the laser device (26). According to the invention, the optical fiber device (280) is designed and arranged in the region of the laser device (26) in such a way that radiation (70) which is incident in the region of the laser device (26) and/or in the region of a combustion chamber (14) associated with the laser device can be injected into the optical fiber device (280). The disclosed design and arrangement of the optical fiber device advantageously allow the radiation that is injected into the optical fiber device to be analyzed, in particular by a detector that is disposed at a distance, without having to provide additional, separate optical fiber devices for the radiation that is ...

Laser ignition system and method for internal combustion engine

Laser ignition system and method for internal combustion engine

A laser beam ignition system 10 for an internal combustion engine 100 is provided. The laser beam ignition system 10 comprises a laser 11 configured to generate a laser beam, and a beam steering unit 12 comprising a lens 22 and a prism 23 both configured to cooperatively transmit the laser beam to focus on an oxygenated fuel mixture supplied into a combustion chamber 101 of the internal combustion engine 100. A method for igniting a fuel mixture in an internal combustion engine 100 is also presented. A System which can focus and direct a plurality of beams is also disclosed.

Laser ignition system and method for internal combustion engine

Laser augmented turbojet propulsion system

The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the aft end of said turbine section. A fuel delivery system is incorporated for supplying fuel to the combustion section. A laser assembly provides electromagnetic radiation to the combustion section. An electrical generator coupled to the turbine driven shaft powers the laser assembly.

COMBUSTION CHAMBER DEVICE, AND METHOD FOR THE OPERATION OF A COMBUSTION CHAMBER DEVICE

Disclosed is a combustion chamber device comprising at least one combustion chamber, at least one injection head that has at least one injector for feeding fuel and oxidant to a combustion chamber, and a laser apparatus for generating at least one laser beam for igniting a fuel-oxidant mixture. In order to design a combustion chamber device that allows for a reliable ignition process in order to ignite a flame, the at least one injector encompasses at least one internal injector element, an external injector element, and a common fluid duct for fluids conducted within the internal injector element and the external injector element. Said common fluid duct leads into the combustion chamber, and the at least one igniting laser beam is injected into the injector in the common fluid duct.

Laserzündsystem und -verfahren für eine Brennkraftmaschine

Es ist ein Laserstrahlzündsystem (10) für eine Brennkraftmaschine (100) geschaffen. Das Laserstrahlzündsystem (10) weist einen Laser (11), der konfiguriert ist, um einen Laserstrahl zu erzeugen, und eine Strahlsteuerungseinheit (12) auf, die eine Linse (22) und ein Prisma (23, 24) aufweist, die beide konfiguriert sind, um den Laserstrahl gemeinsam derart zu übertragen, dass dieser an einem sauerstoffhaltigen Brennstoffgemisch fokussiert wird, der in eine Brennkammer (101) der Brennkraftmaschine (100) geliefert wird. Ein Verfahren zum Zünden eines Brennstoffgemisches in einer Brennkraftmaschine (100) wird ebenfalls präsentiert.

Gas turbine combustor including laser ignition

A combustor according to an embodiment includes: a cylinder body that demarcates a space between a combustor casing and a combustor liner; a pipe that guides a combustion gas between the combustor liner and the cylinder body; a pipe that guides a combustion gas having a temperature lower than a combustion gas to be guided to the pipe between the combustor casing and the cylinder body; a pipe-shaped member provided so as to penetrate the combustor casing, the cylinder body, and the combustor liner; a heat-resistant glass that is provided in the pipe-shaped member; a condensing lens provided in a manner to face the heat-resistant glass; and a laser oscillator that emits laser light to the inside of the combustor liner through the condensing lens.

LASER IGNITION SYSTEM AND METHOD FOR INTERNAL COMBUSTION ENGINE

PROBLEM TO BE SOLVED: To prevent poor combustion from being caused by extinction of flame, ignition on a wall face or around the wall face due to heat loss of an electrode of an ignition plug, or the like. SOLUTION: A laser beam ignition system 10 for an internal combustion engine 100 is provided. The laser beam ignition system 10 includes a laser 11 figured to generate a laser beam, and a beam steering unit 12 comprising a lens and a prism both configured to cooperatively transmit the laser beam to focus on an oxygenated fuel mixture supplied into a combustion chamber 101 of the internal combustion engine 100. A method for igniting a fuel mixture in the internal combustion engine 100 is also presented. COPYRIGHT: (C)2011,JPO&INPIT ...

Laser initiated non-linear fuel droplet ignition

Combustor with an igniter provided within at least one of a fuel injector or a compressed air passage

A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.

Systems involving fiber optic igniters transmitting fuel and laser light

A gas turbine engine system comprising, a gas turbine engine including a combustion area, a laser, a fuel nozzle including an optical fiber operative to transmit light emitted from the laser to the combustion area, the optical fiber also transmitting a fuel into the combustion area, wherein the light is operative to ignite the fuel in the combustion area.

For the stability of the combustion of the auxiliary laser ignition

COMBUSTION CHAMBER DEVICE, AND METHOD FOR THE OPERATION OF A COMBUSTION CHAMBER DEVICE

Disclosed is a combustion chamber device comprising at least one combustion chamber, at least one injection head that has at least one injector for feeding fuel and oxidant to a combustion chamber, and a laser apparatus for generating at least one laser beam for igniting a fuel-oxidant mixture. In order to design a combustion chamber device that allows for a reliable ignition process in order to ignite a flame, the at least one injector encompasses at least one internal injector element, an external injector element, and a common fluid duct for fluids conducted within the internal injector element and the external injector element. Said common fluid duct leads into the combustion chamber, and the at least one igniting laser beam is injected into the injector in the common fluid duct.

Laser initiated non-linear fuel droplet ignition method

Method for igniting an air/fuel spray (26) comprised of fuel droplets including a coherent optical source (12) for introducing at least one pulse of coherent radiation into the air/fuel spray. The pulse generates free electrons and initiates a development of a plasma within the air/fuel spray. The coherent source maintains the pulse of coherent radiation and pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy and before ignition of the air/fuel spray. The non-linear ignition system of the invention employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends from and exists outside of a fuel droplet. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time an avalanche process occurs ...

Laser initiated non-linear fuel droplet ignition

Method and apparatus for igniting an air/fuel spray (26) comprised of fuel droplets. The apparatus includes a coherent optical source (12) for introducing at least one pulse of coherent radiation into the air/fuel spray. The pulse generates free electrons and initiates a development of a plasma within the air/fuel spray. The coherent source maintains the pulse of coherent radiation and pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy and before ignition of the air/fuel spray. The non-linear ignition system of the invention employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends from and exists outside of a fuel droplet. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time ...

Gleichraumbrennkammer

BURNER WITH TORCH IGNITION MECHANISM AND OPERATION METHOD THEREOF

In a burner 1 of an embodiment, a torch part 10 includes: a torch combustor liner 35 that is provided in a torch part casing and burns a fuel and an oxidant; a torch fuel supply part 25 that supplies a fuel; a torch oxidant supply part 20 that supplies an oxidant; an ignition device that ignites a fuel-air mixture; and a combustion gas pipe 40 that is arranged at the center of the torch part 10 and leads a combustion gas in the torch combustor liner 35 to one end side of the torch part 10. Amain fuel-main oxidant supply part 90 includes: a main fuel supply passage 100 formed in an annular shape on an outer periphery of the torch part 10; and a main oxidant supply passage 110 formed in an annular shape on an outer periphery of the main fuel supply passage 100.

Brennkammervorrichtung und Verfahren zu deren Betrieb

Um ein Verfahren zum Betrieb einer Brennkammervorrichtung bereitzustellen, bei welchem ein Zündvorgang zum Zünden einer Flamme zuverlässig mehrfach ausführbar ist, wird vorgeschlagen, dass ein Brennstoff-Oxidator-Gemisch erzeugt wird und mindestens ein Laserstrahl auf das Brennstoff-Oxidator-Gemisch zum Zünden desselben gerichtet wird.

Brennkammervorrichtung

STEUERGERÄT EINES LASERGEZÜNDETEN MOTORS

Ein Steuergerät (ECU (50)) eines lasergezündeten Motors, das ausgelegt ist, um Zündung unter Verwenden einer Laserzündvorrichtung (11) durchzuführen, die ausgelegt ist, um einen durch eine Linse (11d) verdichteten Laserstrahl zu emittieren, umfasst: einen Abschnitt zum Erfassen eines mit einem Verbrennungszustand in Verbindung stehenden Werts (51), der ausgelegt ist, um einen mit einem Verbrennungszustand in Verbindung stehenden Wert, der mit einem Verbrennungszustand des Motors (1) in Verbindung steht, zu erfassen; und einen Verschmutzungsermittlungsabschnitt (52), der ausgelegt ist, um den mit dem Verbrennungszustand in Verbindung stehenden Wert, der von dem Abschnitt zum Erfassen eines mit einem Verbrennungszustand in Verbindung stehenden Werts (51) erfasst wird, mit einem Verbrennungszustandermittlungswert zu vergleichen, um zu ermitteln, ob die Laserzündvorrichtung (11) verschmutzt ist oder nicht, wobei der Verbrennungszustandermittlungswert beruhend auf dem Verbrennungszustand des ...

Ignition device in particular for an internal combustion engine, and method for manufacturing same

An ignition device, for an internal combustion engine of a motor vehicle, having a laser device for generating laser pulses, and having an optical fiber device which is at least optically connected to the laser device for supplying the laser device with pumped light. The optical fiber device is configured and situated in the region of the laser device such that radiation incident in the region of the laser device and/or in the region of a combustion chamber associated with the laser device is injected into the optical fiber device. The optical fiber device advantageously allow the radiation which is injected into the optical fiber device to be analyzed, using a detector which is remotely situated, without having to provide additional, separate optical fiber devices for the radiation to be analyzed, because is conducted directly via the same optical fiber that is already used for supplying pumped light.

Advanced optics and optical access for laser ignition for gas turbines including aircraft engines

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.

内燃エンジン用レーザー点火システム及び方法

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.

Brennkammervorrichtung und Verfahren zu deren Betrieb

Um ein Verfahren zum Betrieb einer Brennkammervorrichtung bereitzustellen, bei welchem ein Zündvorgang zum Zünden einer Flamme zuverlässig mehrfach ausführbar ist, wird vorgeschlagen, dass ein Brennstoff-Oxidator-Gemisch erzeugt wird und mindestens ein Laserstrahl auf das Brennstoff-Oxidator-Gemisch zum Zünden desselben gerichtet wird.

SUPPLEMENTARY LASER FIRING FOR COMBUSTION STABILITY

The present invention relates to a combustion system for a gas turbine. The combustion system comprises a combustion chamber (100) having an end section (101) and a pre-combustion section (102) extending from the end section (101) along a centre axis (103) of the combustion chamber (100), a swirler device (110), an optional pilot burner device (120) and a light emitting arrangement (130). The swirler device (110) is mounted to the pre-combustion section (102) such that a main fuel (111) is injectable by or through the swirler device (110) into an inner volume (104) of the pre- combustion section (102). The main flame (108) using the main fuel (111) is producible inside the inner volume (104). The optional pilot burner device (120) is mounted to the end section (101) of the combustion chamber (100) such that a pilot fuel (121) is injectable by or through the pilot burner device (120) into the inner volume (104) of the pre-combustion section (102), wherein a pilot flame (122) using the pilot ...

Laser initiated non-linear fuel droplet ignition

Method and apparatus for igniting an air/fuel spray (26) comprised of fuel droplets. The apparatus includes a coherent optical source (12) for introducing at least one pulse of coherent radiation into the air/fuel spray. The pulse generates free electrons and initiates a development of a plasma within the air/fuel spray. The coherent source maintains the pulse of coherent radiation and pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy and before ignition of the air/fuel spray. The non-linear ignition system of the invention employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends from and exists outside of a fuel droplet. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time ...

CONTROLLER OF LASER IGNITION ENGINE

A controller of a laser ignition engine configured to perform ignition by using a laser ignition device configured to emit a laser beam condensed by a lens includes: a combustion state related value acquiring portion configured to acquire a combustion state related value related to a combustion state of the engine; and a contamination determining portion configured to compare the combustion state related value acquired by the combustion state related value acquiring portion with a combustion state determining value to determine whether or not the laser ignition device is contaminated, the combustion state determining value being defined based on the combustion state of the engine when the laser ignition device is not contaminated. 1. A controller of a laser ignition engine configured to perform ignition by using a laser ignition device configured to emit a laser beam condensed by a lens ,the controller comprising:a combustion state related value acquiring portion configured to acquire a combustion state related value that is related to a combustion state of the engine and changes in accordance with a position of an ignition point; anda contamination determining portion configured to compare the combustion state related value acquired by the combustion state related value acquiring portion with a combustion state determining value to determine whether or not the laser ignition device is contaminated, the combustion state determining value being defined based on the combustion state of the engine when the laser ignition device is not contaminated.2. The controller according to claim 1 , wherein:the combustion state related value acquiring portion acquires, as the combustion state related value, cylinder internal pressure detected by a cylinder internal pressure sensor provided at the engine;the contamination determining portion uses, as the combustion state determining value, a cylinder internal pressure determining value defined based on the cylinder internal ...

IGNITION AND CHEMICAL REACTION ACCELERATOR AND FLAME STABILIZER, SPEED-TYPE INTERNAL COMBUSTION ENGINE, AND FURNACE

An ignition and chemical reaction accelerator and flame stabilizer which can drastically improve ignition, flame expansion, and flame stabilization in a speed-type internal combustion engine such as gas turbines, ram facilities, and rocket engines, and a high-performance speed-type internal combustion engine using the same. The ignition and chemical reaction accelerator and flame stabilizer for a speed-type internal combustion engine comprises a spark plug (110) for preparing charged particles at a specified position inside a combustor (104) of a speed-type internal combustion engine, a microwave oscillator (116) for inducing plasmas, a material of which is a working fluid in the combustor, by emitting a microwave pulse toward the charged particles and the perimeter thereof, and an antenna (112). In the ignition and chemical reaction accelerator and flame stabilizer, a region satisfying sufficient conditions for combustion inside the combustor is formed by supplying active chemical species ...

Laser ignition system and method for internal combustion engine

A laser beam ignition system for an internal combustion engine is provided. The laser beam ignition system comprises a laser configured to generate a laser beam, and a beam steering unit comprising a lens and a prism both configured to cooperatively transmit the laser beam to focus on an oxygenated fuel mixture supplied into a combustion chamber of the internal combustion engine. A beam steering unit and a method for igniting a fuel mixture in an internal combustion engine are also presented.

Zündeinrichtung insbesondere für eine Brennkraftmaschine und Herstellungsverfahren hierfür

Die Erfindung betrifft eine Zündeinrichtung (27), insbesondere für eine Brennkraftmaschine eines Kraftfahrzeugs, mit einer Lasereinrichtung (26) zur Erzeugung von Laserimpulsen (24) und mit einer mit der Lasereinrichtung (26) zumindest optisch verbundenen Lichtleitereinrichtung (280) zur Versorgung der Lasereinrichtung (26) mit Pumplicht (60). Erfindungsgemäß ist die Lichtleitereinrichtung (280) so ausgebildet und in dem Bereich der Lasereinrichtung (26) angeordnet, dass im Bereich der Lasereinrichtung (26) und/oder im Bereich eines der Lasereinrichtung (26) zugeordneten Brennraums (14) auftretende Strahlung (70) in die Lichtleitereinrichtung (280) einkoppelbar ist.

GAS TURBINE COMBUSTOR

A combustor according to an embodiment includes: a cylinder body that demarcates a space between a combustor casing and a combustor liner; a pipe that guides a combustion gas between the combustor liner and the cylinder body; a pipe that guides a combustion gas having a temperature lower than a combustion gas to be guided to the pipe between the combustor casing and the cylinder body; a pipe-shaped member provided so as to penetrate the combustor casing, the cylinder body, and the combustor liner; a heat-resistant glass that is provided in the pipe-shaped member; a condensing lens provided in a manner to face the heat-resistant glass; and a laser oscillator that emits laser light to the inside of the combustor liner through the condensing lens.

Commonly housed electrostatic fuel atomizer and igniter apparatus for combustors

Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main fuel nozzle is provided which includes a plurality of electrostatic fuel nozzles disposed about a centrally located igniter. In one embodiment, the igniter is a laser igniter.

Ignition/chemical reaction promotion/flame holding device, speed-type internal combustion engine, and furnace

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 ...

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.

IGNITION AND CHEMICAL REACTION ACCELERATOR AND FLAME STABILIZER, SPEED-TYPE INTERNAL COMBUSTION ENGINE, AND FURNACE

PROBLEM TO BE SOLVED: To provide an ignition and chemical reaction accelerator and flame stabilizer, which drastically improves ignition, flame expansion, and flame stabilization in a speed-type internal combustion engine such as gas turbines, ram facilities, and rocket engines, and also to provide a high-performance speed-type internal combustion engine using the same. SOLUTION: The ignition and chemical reaction accelerator and flame stabilizer for a speed-type internal combustion engine comprises: a spark plug 110 for preparing charged particles at a specified position inside a combustor 104 of a speed-type internal combustion engine; a microwave oscillator 116 for inducing plasmas, the material of which is a working fluid in the combustor, by emitting a microwave pulse toward the charged particles and the perimeter thereof; and an antenna 112. In the ignition and chemical reaction accelerator and flame stabilizer, a region satisfying sufficient conditions for combustion inside the combustor ...

Advanced Optics and Optical Access for Laser Ignition for Gas Turbines Including Aircraft Engines

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.

Apparatus and method for igniting a combustor

A nozzle includes a center body that defines an axial centerline. A shroud circumferentially surrounds at least a portion of the center body to define an annular passage between the center body and the shroud. A plenum is inside the center body and substantially parallel to the axial centerline, and an igniter is inside the center body and generally adjacent to the plenum. A method for igniting a combustor includes flowing a fuel through a center body axially aligned in a nozzle and flowing a working fluid through an annular passage, wherein the annular passage is substantially parallel to and radially outward of the center body. The method further includes projecting at least one of a beam, spark, or flame from an igniter located inside the center body.

Supplementary Laser Firing for Combustion Stability

The present invention relates to a combustion system for a gas turbine. The combustion system comprises a combustion chamber (100) having an end section (101) and a pre-combustion section (102) extending from the end section (101) along a centre axis (103) of the combustion chamber (100), a swirler device (110), an optional pilot burner device (120) and a light emitting arrangement (130). The swirler device (110) is mounted to the pre-combustion section (102) such that a main fuel (111) is injectable by or through the swirler device (110) into an inner volume (104) of the pre-combustion section (102). The main flame (108) using the main fuel (111) is producible inside the inner volume (104). The optional pilot burner device (120) is mounted to the end section (101) of the combustion chamber (100) such that a pilot fuel (121) is injectable by or through the pilot burner device (120) into the inner volume (104) of the pre-combustion section (102), wherein a pilot flame (122) using the pilot ...

DEVICE FOR IGNITION, CHEMICAL REACTION ACCELERATION OR FLAME HOLDING, SPEED-TYPE INTERNAL COMBUSTION ENGINE AND FURNACE

Electrostatic fuel injector body with igniter electrodes formed in the housing

Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main fuel nozzle is provided which includes a plurality of electrostatic fuel nozzles disposed about a centrally located igniter. In one embodiment, the igniter is a laser igniter.

Low energy laser-induced ignition of an air-fuel mixture

A new approach for igniting an air-fuel mixture in a turbine or other engine is disclosed. Resonance-enhanced multiphoton ionization (REMPI) is used to generate volume ionization within an air-fuel flow and induce an ignition arc. The output of a relatively low energy single pulsed ultraviolet laser is aimed across an electric field inside a volume of air to create a pre-ionized channel so that a smaller voltage electric field is sufficient to create an electrical arc that follows the pre-ionized channel and will ignite an air-fuel mixture. Because the arc follows the pre-ionized channel, it can be directed to an optimal location inside an ignition volume for igniting the air-fuel mixture. A specific example embodiment is described using a 287.5 nm wavelength pulsed ultraviolet laser to excite ground state oxygen molecules to a specific excited state having a coincident term energy with a specific nitrogen molecule excited state.

GAS TURBINE VARIABLE FOCUS LASER IGNITION

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.

Laser-ignition combustor for gas turbine engine

A combustor (16) has a laser ignitor (40) mounted to a casing (20), remotely from a liner (24) of the combustion chamber. The laser ignitor (40) has an igniter beam path (46) for igniting the fuel and air mixture in the combustion chamber (16), the igniter beam path (46) extending at least partially across the air plenum (28) surrounding the liner (24) and into the combustion chamber (16) through a corresponding beam path aperture (46) provided in the liner (24).

Ignition methods and apparatus for combustors

Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main fuel nozzle is provided which includes a plurality of electrostatic fuel nozzles disposed about a centrally located igniter. In one embodiment, the igniter is a laser igniter.

Gas turbine engine photon ignition system

A photon ignition system for igniting the air/fuel spray within a combustion chamber of a gas turbine engine is comprised of a photon source 20, a photon transmission means 22 and a focussing means 24. The source 20 has an output wavelength characteristic suitable for being absorbed by the hydrocarbon fuel droplets within the fuel spray. In accordance with one embodiment of the invention the source 20 comprises an ultraviolet flashlamp having spectral characteristics which are selected to be strongly absorbed by hydrocarbon fuel. In another embodiment of the invention the source 20 comprises a laser, such an excimer laser, having an output pulse with wavelengths within the strong absorption range of hydrocarbon fuel. The photon output of the source 20 is focussed within an optimum region of the fuel spray for igniting one or more droplets therein due to the absorption and subsequent heating of the droplets of the focussed photon output.

IGNITION AND CHEMICAL REACTION ACCELERATOR AND FLAME STABILIZER, 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 (110) for preparing charged particles in a predetermined location in a combustor (104) of the speed-type internal combustion engine, and a microwave oscillator (116) and antenna (112) 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 ...

Laser-charged high-speed propulsion system and method for production of high-powered laser

A high-speed propulsion system for a high-speed vehicle includes an air intake duct, a compression section, a combustion section, and an expansion section. A gas dynamic laser generator is disposed proximate the expansion section and generates a source of laser light. A laser transmission mechanism receives the laser light and transmits the laser light from the gas dynamic laser generator to the combustion section and to presents the laser light into the air/fuel mixture of the flowpath which promotes mixing, combustion, and flame stability.

APPARATUS AND METHOD FOR IGNITING A COMBUSTOR

A nozzle includes a center body that defines an axial centerline. A shroud circumferentially surrounds at least a portion of the center body to define an annular passage between the center body and the shroud. A plenum is inside the center body and substantially parallel to the axial centerline, and an igniter is inside the center body and generally adjacent to the plenum. A method for igniting a combustor includes flowing a fuel through a center body axially aligned in a nozzle and flowing a working fluid through an annular passage, wherein the annular passage is substantially parallel to and radially outward of the center body. The method further includes projecting at least one of a beam, spark, or flame from an igniter located inside the center body.

Laser initiated non-linear fuel droplet ignition

Method and apparatus for igniting an air/fuel spray (26) comprised of fuel droplets. The apparatus includes a coherent optical source (12) for introducing at least one pulse of coherent radiation into the air/fuel spray. The pulse generates free electrons and initiates a development of a plasma within the air/fuel spray. The coherent source maintains the pulse of coherent radiation and pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy and before ignition of the air/fuel spray. The non-linear ignition system of the invention employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends from and exists outside of a fuel droplet. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time ...

Laser ignition system

A device that includes a window, a catalyzed layer, and a laser source is disclosed. The window may include a first surface and a second surface. The catalyzed layer may be disposed on the first surface of the window. The catalyzed layer may include a compound having a threshold transmittance, and be configured to cause a reaction with soot in one or more of a combustion chamber or a pre-combustion chamber of a combustion engine at an activation temperature to reduce accumulation of soot on the window. The laser source may be disposed relative to the second surface of the window, and configured to emit a laser beam through the window and the catalyzed layer. The laser beam may be configured to cause ignition of an intake charge of one or more of the combustion chamber or the pre-combustion chamber.

Supplementary laser firing for combustion stability

Laser augmented turbojet propulsion system

The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the aft end of said turbine section. A fuel delivery system is incorporated for supplying fuel to the combustion section. A laser assembly provides electromagnetic radiation to the combustion section. An electrical generator coupled to the turbine driven shaft powers the laser assembly.

Laser ignition system

Advanced laser ignition systems for gas turbines including aircraft engines

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system comprises at least one laser light source configured to generate a laser beam and an optical beam guidance component. The optical beam guidance component is configured to transmit the laser beam to irradiate on an oxygenated fuel mixture supplied into the combustion chamber at a region of highest ignitability to generate a combustor flame in a flame region. The system further includes an integrated control diagnostic component configured to detect at least a portion of a light emission and operable to control one or more combustion parameters based in part on the detected light emission. The system further includes additional enhanced ignition control configurations. A method for igniting a fuel mixture in an internal combustion engine is also presented.

Injection device for an internal combustion engine

An injection device for injecting fuel into a combustion chamber, includes: a housing rigidly connected to the combustion chamber, an injection part rotatably connected to the housing and drivable by an actuator in order to rotate with respect to the housing about a central axis, a supply conduit fluidically connected to the combustion chamber for the pressurized introduction of a fuel into the combustion chamber and which includes a fluid-tight coupling between the housing and the injection part; an injection nozzle rigidly connected to the injection part and which includes an atomizer having an atomizer opening fluidically connected to the supply conduit for introducing fuel into the combustion chamber, whereas the injection nozzle rotates, and at least one further supply conduit for the pressurized introduction of a fluid into the combustion chamber.

Laser ignition system

A device that includes a window, a catalyzed layer, and a laser source is disclosed. The window may include a first surface and a second surface. The catalyzed layer may be disposed on the first surface of the window. The catalyzed layer may include a compound having a threshold transmittance, and be configured to cause a reaction with soot in one or more of a combustion chamber or a pre-combustion chamber of a combustion engine at an activation temperature to reduce accumulation of soot on the window. The laser source may be disposed relative to the second surface of the window, and configured to emit a laser beam through the window and the catalyzed layer. The laser beam may be configured to cause ignition of an intake charge of one or more of the combustion chamber or the pre-combustion chamber.

Controller of laser ignition engine

A controller of a laser ignition engine configured to perform ignition by using a laser ignition device configured to emit a laser beam condensed by a lens includes: a combustion state related value acquiring portion configured to acquire a combustion state related value related to a combustion state of the engine; and a contamination determining portion configured to compare the combustion state related value acquired by the combustion state related value acquiring portion with a combustion state determining value to determine whether or not the laser ignition device is contaminated, the combustion state determining value being defined based on the combustion state of the engine when the laser ignition device is not contaminated.

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 (110) for preparing charged particles in a predetermined location in a combustor (104) of the speed-type internal combustion engine, and a microwave oscillator (116) and antenna (112) 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 ...

Laser initiated non-linear fuel droplet ignition apparatus

Apparatus for igniting an air/fuel spray (26) comprised of fuel droplets. The apparatus includes a coherent optical source (12) for introducing at least one pulse of coherent radiation into the air/fuel spray. The pulse generates free electrons and initiates a development of a plasma within the air/fuel spray. The coherent source maintains the pulse of coherent radiation and pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy and before ignition of the air/fuel spray. The non-linear ignition system of the invention employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends from and exists outside of a fuel droplet. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time an avalanche ...

Laser augmented turbojet propulsion system

The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the aft end of said turbine section. A fuel delivery system is incorporated for supplying fuel to the combustion section. A laser assembly provides electromagnetic radiation to the combustion section. An electrical generator coupled to the turbine driven shaft powers the laser assembly.

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.

Laser ignition engine control device

本发明是使用发射由透镜（11d）聚光的激光的激光点火装置（11）进行点火的激光点火式发动机的控制装置（ECU（50）），具有：获得与发动机（1）的燃烧状态相关的燃烧状态相关值的燃烧状态相关值获得部（51）；和将由燃烧状态相关值获得部（51）获得的燃烧状态相关值、与基于激光点火装置（11）未被污染的状态下的发动机的燃烧状态而规定的燃烧状态判定值相比较，判定激光点火装置（11）是否被污染的污染判定部（52）。

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.

Supplementary laser firing for combustion stability

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.

Control device for laser ignition engine

ADVANCED OPTICS AND OPTICAL ACCESS FOR LASER IGNITION SYSTEM FOR GAS TURBINE INCLUDING AIRCRAFT ENGINE

PROBLEM TO BE SOLVED: To provide a laser ignition system for an internal combustion engine, and more specifically a gas turbine engine. SOLUTION: The system includes a laser light source configured to generate a laser beam, an ignition port configured to optimize optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting the fuel mixture in the internal combustion engine is also presented. COPYRIGHT: (C)2012,JPO&INPIT ...

DEVICE AND METHOD FOR IGNITING A COMBUSTION SYSTEM

Injecteur (30) comprenant un corps central (32) qui définit un axe géométrique central (38). Une enveloppe (34) entoure le pourtour d'au moins une partie du corps central (32) afin de définir un passage annulaire (40) entre le corps central (32) et l'enveloppe (34). Un volume (44, 46) se trouve à l'intérieur du corps central (32) et sensiblement parallèlement à l'axe géométrique central (38), et un allumeur (52) se trouve à l'intérieur du corps central (32), globalement au voisinage immédiat du volume (44, 46). Un procédé pour allumer un système de combustion comporte l'écoulement d'un combustible dans un corps central (32) aligné axialement dans un injecteur (30) et l'écoulement d'un fluide de travail dans un passage annulaire (40), le passage annulaire (40) étant sensiblement parallèle au corps central (32) et radialement à l'extérieur du corps central. Le procédé comporte en outre la projection d'un faisceau et/ou d'une étincelle et/ou d'une flamme depuis un allumeur (52) situé à l'intérieur du corps central (32). Injector (30) comprising a central body (32) which defines a central geometric axis (38). An envelope (34) surrounds the periphery of at least a portion of the central body (32) to define an annular passage (40) between the central body (32) and the envelope (34). A volume (44, 46) is located within the central body (32) and substantially parallel to the central geometric axis (38), and an igniter (52) is located within the central body (32) , generally in the immediate vicinity of the volume (44, 46). A method for igniting a combustion system includes flowing fuel into a central body (32) aligned axially in an injector (30) and flowing a working fluid into an annular passage (40), the annular passage (40) being substantially parallel to the central body (32) and radially outside the central body. The method further includes projecting a beam and / or a spark and / or a flame from an igniter (52) ...

Excitation of an additional laser for combustion stability

FIELD: power engineering. SUBSTANCE: invention relates to power engineering. Burning system comprises combustion chamber (100), which has end section (101) and combustion pre-section (102), continuing from end section (101) along central axis (103) of combustion chamber (100), turbulized element (110), optional ignition burner device (120) and light-emitting device (130) which emits in internal volume (104) of combustion pre-section (102) electromagnetic radiation (131), characterized by the fact that it can generate energy supply in ignition flame (122) or main flame (108) for stabilisation of ignition flame (122) or main flame (108). Also disclosed is a method of controlling a gas turbine combustion system. EFFECT: invention provides reduced amount of fuel required for the ignition flame, reduced emissions, and also enables to achieve stable combustion process. 13 cl, 4 dwg

DEVICE AND METHOD FOR IGNITING A COMBUSTION SYSTEM

Supplementary laser firing for combustion stability

The present invention relates to a combustion system for a gas turbine. The combustion system comprises a combustion chamber (100) having an end section (101) and a pre-combustion section (102) extending from the end section (101) along a centre axis (103) of the combustion chamber (100), a swirler device (110), an optional pilot burner device (120) and a light emitting arrangement (130). The swirler device (110) is mounted to the pre-combustion section (102) such that a main fuel (111) is injectable by or through the swirler device (110) into an inner volume (104) of the pre- combustion section (102). The main flame (108) using the main fuel (111) is producible inside the inner volume (104). The optional pilot burner device (120) is mounted to the end section (101) of the combustion chamber (100) such that a pilot fuel (121) is injectable by or through the pilot burner device (120) into the inner volume (104) of the pre-combustion section (102), wherein a pilot flame (122) using the pilot fuel (121) is producible inside the inner volume (104) for stabilizing the main flame (108). The light emitting arrangement (130) emits an electromagnetic radiation (131) into the inner volume (104), wherein the light emitting arrangement (130) is arranged to the combustion chamber (100) such that an energy input to the pilot flame (122) and/or the main flame (108) is generatable by the electromagnetic radiation (131) for stabilizing the pilot flame (122) and/or the main flame (108), particularly to reduce the fuel required by the pilot flame and hence the emissions. The light emitting arrangement could also be used to replace the function of the pilot flame and be used to stabilise the main flame instead of using a pilot flame.

具有点火器的燃烧器

一种涡轮发动机，包括处于串行流动布置的压缩机区段、具有燃烧器的燃烧区段、和涡轮区段。燃烧器具有燃烧室、至少一个燃料喷射器、至少一个压缩空气通道和至少一个点火器。至少一个点火器可以设置在至少一个燃料喷射器或至少一个压缩空气通道的一部分内。

Laserzündsystem

Burner with torch ignition mechanism and operation method thereof

In a burner of an embodiment, a torch part includes: a torch combustor liner that is provided in a torch part casing and burns a fuel and an oxidant; a torch fuel supply part that supplies a fuel; a torch oxidant supply part that supplies an oxidant; an ignition device that ignites a fuel-air mixture; and a combustion gas pipe that is arranged at the center of the torch part and leads a combustion gas in the torch combustor liner to one end side of the torch part. A main fuel-main oxidant supply part includes: a main fuel supply passage formed in an annular shape on an outer periphery of the torch part; and a main oxidant supply passage formed in an annular shape on an outer periphery of the main fuel supply passage.

[UNK]

Laser initiated non-linear fuel droplet ignition

Method and apparatus for igniting an air/fuel spray (26) including a coherent optical source (12) for introducing at least one pulse of radiation into the spray to generate free electrons and initiate development of a plasma. The coherent source pumps the developing plasma to higher energies. The pulse is terminated at a time after the plasma has reached a predetermined energy level. This non-linear ignition system employs a gas/vapor interface region at a fuel droplet surface and an electric field that extends outwardly from the fuel droplet surface. Free electrons are accelerated to higher energies by the electric field surrounding the fuel droplet. The accelerated electrons initiate a breakdown near adjacent fuel droplets and the liberation of further free electrons. In a short period of time an avalanche process occurs that creates a high density of free electrons and ions which results in the formation of plasma.

具有点火器的燃烧器

一种涡轮发动机，包括处于串行流动布置的压缩机区段、具有燃烧器的燃烧区段、和涡轮区段。燃烧器具有燃烧室、至少一个燃料喷射器、至少一个压缩空气通道和至少一个点火器。至少一个点火器可以设置在至少一个燃料喷射器或至少一个压缩空气通道的一部分内。

激光点火系统

公开了一种包括窗口、催化层和激光源的装置。该窗口可以包括第一表面和第二表面。该催化层可以设置在该窗口的第一表面上。该催化层可以包括具有阈值透射率的化合物，并且被配置为用于在激活温度下引起与燃烧发动机的燃烧室或预燃烧室中的一个或多个中的碳烟的反应以减少碳烟在该窗口上的累积。该激光源可以相对于该窗口的第二表面被设置，并且被配置为发射通过该窗口和该催化层的激光束。该激光束可以被配置为引起该燃烧室或该预燃烧室中的一个或多个的进气充气的点火。

Burner with torch ignition mechanism and operation method thereof

激光点火系统

公开了一种包括窗口、催化层和激光源的装置。该窗口可以包括第一表面和第二表面。该催化层可以设置在该窗口的第一表面上。该催化层可以包括具有阈值透射率的化合物，并且被配置为用于在激活温度下引起与燃烧发动机的燃烧室或预燃烧室中的一个或多个中的碳烟的反应以减少碳烟在该窗口上的累积。该激光源可以相对于该窗口的第二表面被设置，并且被配置为发射通过该窗口和该催化层的激光束。该激光束可以被配置为引起该燃烧室或该预燃烧室中的一个或多个的进气充气的点火。