| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Symmetric fuel injection for turbine combustor | US13345825 | 2012-01-09 | US09062609B2 | 2015-06-23 | Carsten Ralf Mehring; James Peffley |
| A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture. | ||||||
| 22 | SYMMETRIC FUEL INJECTION FOR TURBINE COMBUSTOR | US13345825 | 2012-01-09 | US20130174559A1 | 2013-07-11 | Carsten Ralf Mehring; James Peffley |
| A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture. | ||||||
| 23 | SYSTEMS AND METHODS INVOLVING IMPROVED FUEL ATOMIZATION IN AIR BLAST FUEL NOZZLES OF GAS TURBINE ENGINES | US13657088 | 2012-10-22 | US20130074514A1 | 2013-03-28 | Jeffery A. Lovett; Frederick C. Padget; John W. Mordosky; Shawn M. McMahon |
| Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface. | ||||||
| 24 | APPARATUS AND METHOD FOR VARYING THE PROPERTIES OF A MULTIPLE-PHASE JET | US12812412 | 2009-01-09 | US20100276507A1 | 2010-11-04 | Bernard Labegorre; Thierry Poinsot; Nicolas Guezennec |
| The invention relates to an apparatus and a method for injecting a multiple-phase jet with a variable direction and/or opening, by the fluidic interaction between the multiple-phase jet and one or more actuation jets. | ||||||
| 25 | BURNER WITH LANCE | US12437223 | 2009-05-07 | US20090280443A1 | 2009-11-12 | Richard CARRONI; Madhavan Narasimhan POYYAPAKKAM; Michal BIALKOWSKI; Mark Andrew WILLETTS |
| The present invention relates to a burner for a combustion chamber of a gas turbine plant. The burner includes a lance for introducing gaseous fuel into the burner. A shaft of the lance has at least one nozzle for introducing gaseous fuel into the burner. A main injection direction of the respective nozzle is oriented onto a portion of a burner wall. An introduction device for a diverting fluid is provided, which is designed for introducing a diverting fluid counteracting an impingement of the fuel flow on the burner wall. | ||||||
| 26 | Fuel nozzle for a gas turbine engine and method for fabricating the same | US12069870 | 2008-02-12 | US20090199561A1 | 2009-08-13 | William Kirk Hessler |
| A method for fabricating a secondary fuel nozzle assembly includes providing a nozzle portion defining a passageway configured to supply fuel. At least one peg is operatively coupled in fuel flow communication with the passageway. The at least one peg extends radially outward from the nozzle portion and defines at least one opening configured to direct a flow of fuel in a substantially upstream direction. A disc is positioned about the nozzle portion upstream of the at least one peg. The disc is positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization. | ||||||
| 27 | FUEL INJECTOR FOR A GAS TURBINE ENGINE COMBUSTION CHAMBER | US11868176 | 2007-10-05 | US20080083841A1 | 2008-04-10 | Francois Rene Daniel BAINVILLE; Denis Jean Maurice Sandelis; Stephane Henri Guy Touchaud |
| The present invention relates to a fuel injector (100) for a gas turbine engine combustion chamber, comprising a first fuel supply line for running at idle speed, and a second, main, fuel supply line for running at speeds up to full throttle and first (112) and second (113) injection orifices with which the two fuel supply lines respectively communicate. The injector is one wherein the injection orifices (112, 113) are arranged in a ring, the first orifices occupying a sector of said ring. | ||||||
| 28 | Burner | US64711323 | 1923-06-22 | US1578133A | 1926-03-23 | ACHILLE KAIS |
| 29 | Düse für einen Gasbrenner | EP14185135.2 | 2014-09-17 | EP2863121A3 | 2015-07-15 | Ferreira, Ricardo; Zeferina, Vasco; Afonso, Alexandre |
Die Erfindung betrifft eine Düse für einen Gasbrenner, wobei die Düse einen Kanal aufweist, der zum Abgeben von Gas vorgesehen ist, wobei der Kanal an einer Austrittsöffnung endet, wobei ein Strömungselement außerhalb der Austrittsöffnung angeordnet ist, wobei das Strömungselement einen ersten Abschnitt aufweist, der ausgehend von einem ersten Durchmesser in Richtung weg von der Austrittsöffnung bis zu einem zweiten Durchmesser zunimmt, wobei das Strömungselement ausgehend vom zweiten Durchmesser in einem zweiten Abschnitt mit zunehmendem Abstand von der Austrittsöffnung im Durchmesser wieder bis zu einem dritten Durchmesser abnimmt, wobei das Strömungselement rotationssymmetrisch zu einer Mittenachse des Kanals ausgebildet und angeordnet ist.
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| 30 | Düse für einen Gasbrenner | EP14185135.2 | 2014-09-17 | EP2863121A2 | 2015-04-22 | Ferreira, Ricardo; Zeferina, Vasco; Afonso, Alexandre |
Die Erfindung betrifft eine Düse für einen Gasbrenner, wobei die Düse einen Kanal aufweist, der zum Abgeben von Gas vorgesehen ist, wobei der Kanal an einer Austrittsöffnung endet, wobei ein Strömungselement außerhalb der Austrittsöffnung angeordnet ist, wobei das Strömungselement einen ersten Abschnitt aufweist, der ausgehend von einem ersten Durchmesser in Richtung weg von der Austrittsöffnung bis zu einem zweiten Durchmesser zunimmt, wobei das Strömungselement ausgehend vom zweiten Durchmesser in einem zweiten Abschnitt mit zunehmendem Abstand von der Austrittsöffnung im Durchmesser wieder bis zu einem dritten Durchmesser abnimmt, wobei das Strömungselement rotationssymmetrisch zu einer Mittenachse des Kanals ausgebildet und angeordnet ist.
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| 31 | APPAREIL ET PROCEDE POUR FAIRE VARIER LES PROPRIETES D'UN JET MULTIPHASIQUE | EP09704348.3 | 2009-01-09 | EP2249968A1 | 2010-11-17 | LABEGORRE, Bernard; POINSOT, Thierry; GUEZENNEC, Nicolas |
| The invention relates to an apparatus and a method for injecting a multiple-phase jet with a variable direction and/or opening, by the fluidic interaction between the multiple-phase jet and one or more actuation jets. | ||||||
| 32 | Injecteur de carburant pour chambre de combustion de moteur à turbine à gaz | EP07117658.0 | 2007-10-01 | EP1909031A1 | 2008-04-09 | Bainville, François; Sandelis, Denis; Touchaud, Stéphane |
La présente invention porte sur un injecteur (100) de carburant pour chambre de combustion de moteur à turbine à gaz comprenant un premier conduit d'alimentation en carburant pour un fonctionnement au ralenti et un second conduit d'alimentation principal en carburant pour un fonctionnement jusqu'au régime de plein gaz, et des premiers (112) et des seconds (113) orifices d'injection avec lesquels les deux conduits d'alimentation communiquent respectivement. L'injecteur est caractérisé par le fait que les orifices (112, 113) d'injection sont disposés en anneau, les premiers orifices occupant un secteur dudit anneau.
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| 33 | 분무 노즐 및 분무 노즐을 갖는 연소 장치 | KR1020137019390 | 2012-01-12 | KR1020130103798A | 2013-09-24 | 오카자키히로후미; 구라마시코지; 오키모토히데오; 오리이아키히토; 오치겐이치 |
| In a combustion device which sprays liquid fuel and combusts it, an object is to promote combustion reaction and improve combustion efficiency, and suppress exhaustion of ash dust, carbon monoxide, nitrogen oxide, by reducing spray particle diameter and reducing kinetic momentum. A spray nozzle is provided with upper and lower channels 28 and 29 from respective surfaces, the two channels form a cross shape, and become a fuel spray hole by communication of an intersecting part 30. A guide member 23 is provided, in contact with the upstream-side channel 28, in a position overlapped with the intersecting part (fuel spray hole) 30 with respect to the spray direction of the spray nozzle. Spray fluid (liquid fuel) is branched with the guide member 23 from the fuel fluid duct 21 connected to the spray nozzle, passes through the upstream-side channel 28, to the intersecting part 30, and is sprayed. The spray fluid forms opposed flows toward the intersecting part 30 in the upstream-side channel 28 to collide with each other at an obtuse angle of 90° or greater, then is sprayed from the intersecting part 30, to form a thin fan-shaped liquid film 31. The liquid film is divided by a shearing force from the peripheral gas, atomized into spray particles 32. | ||||||
| 34 | 분무 노즐 및 분무 노즐을 갖는 연소 장치 | KR1020137019390 | 2012-01-12 | KR101494989B1 | 2015-02-23 | 오카자키히로후미; 구라마시코지; 오키모토히데오; 오리이아키히토; 오치겐이치 |
| 액체 연료를 분무시켜 연소시키는 연소 장치에 있어서, 분무 입자 직경을 작게 하는 동시에 운동량을 저하시킴으로써 연소 반응을 촉진시켜, 연소 효율을 향상시키는 동시에, 매진이나 일산화탄소, 질소 산화물의 배출을 억제한다. 분무 노즐은 상하에 홈(28, 29)이 각각의 표면으로부터 형성되어 있고, 2개의 홈은 십자 형상이며, 교차부(30)가 연통됨으로써 연료 분출 구멍으로 된다. 안내 부재(23)를 상류측의 홈(28)에 접하고, 분무 노즐의 분출 방향에 대하여, 교차부(연료 분출 구멍)(30)와 겹치는 위치에 설치한다. 분무 유체(액체 연료)는, 분무 노즐에 접속하는 연료 유로(21)로부터 상기 안내 부재(23)에 의해 분기하고 상류측의 홈(28)을 통과하고, 교차부(30)로 흘러 분출한다. 분무 유체는 상류측의 홈(28)에 있어서 교차부(30)를 향하는 대향하는 흐름을 형성하고 90° 이상의 둔각을 이뤄 충돌하고, 교차부(30)로부터 분출하여 얇은 부채 형상의 액막(31)을 형성한다. 액막은 주위의 기체와의 전단력에 의해 분열되고, 미세화되어 분무 입자(32)로 된다.
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| 35 | FUEL LANCE WITH MEANS FOR INTERACTING WITH A FLOW OF AIR AND IMPROVE BREAKAGE OF AN EJECTED LIQUID JET OF FUEL | EP14816023.7 | 2014-11-26 | EP3224544A1 | 2017-10-04 | PORTILLO BILBAO, Juan Enrique |
| Apparatus and method for a combustion turbine engine are provided. The apparatus may include a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) of the lance. At least one jet in cross-flow injector (18) may be disposed at the downstream end of the lance, and includes an ejection orifice (20) responsive to eject a liquid jet (22) of the fuel. A plurality of surface irregularities (28, 29, 30, 50, 52, 54) is disposed at least on a portion of a wall (32) of the fuel-injecting lance exposed to the flow of air and proximate to the ejection orifice (20). The plurality of surface irregularities may be arranged to interact (e.g., turbulent interaction) with the flow of air to promote breakage of the ejected liquid jet of fuel compared to an injector lacking such surface irregularities. | ||||||
| 36 | Burner with lance | EP08103889.5 | 2008-05-09 | EP2116767B1 | 2015-11-18 | Carroni, Richard; Poyyapakkam, Madhavan Narasimhan; Bialkowski, Michal Tadeusz; Willets, Mark |
| 37 | Ölvormischbrenner | EP10171578.7 | 2010-08-02 | EP2282116A2 | 2011-02-09 | Rausch, Rainer; Szczyra, Gregor; Schuessler, Michael; Cecen, Sadik |
Die Erfindung betrifft einen Ölvormischbrenner mit einem im Wesentlichen zylindrischen Brennelement (1), einer Brenneroberfläche (2) auf der äußeren Mantelfläche, einem stirnseitigen Deckelelement (3) am freien Ende, einer Verteilkammer (4) unterhalb der Brenneroberfläche (2), einer zentralen, auf der Längsachse des Brennelementes (1) angeordneten Zerstäubungseinrichtung (5), insbesondere ein Einspritzventil oder eine Öldüse, einem an ein stromaufwärts angeordnetes Gebläse angeschlossenen Verbrennungsluftkanal (6) sowie einem Luftwärmetauscher (7) unterhalb der Brenneroberfläche (2) für die Vorwärmung mindestens eines Teilstroms der Verbrennungsluft. Aufgabe der Erfindung ist es, bei einem Ölvormischbrenner die Verbrennungsqualität und die Robustheit, besonders im Hinblick auf Modulationsfähigkeit, zu optimieren. Erfindungsgemäß ist daher vorgesehen, dass ein Prallkörper (8) auf der Längsachse des Brennelementes (1), im direkten Bereich des Flüssigkeitsstrahles mit Abstand vor der Zerstäubungseinrichtung (5) angeordnet ist.
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| 38 | Burner with lance | EP08103889.5 | 2008-05-09 | EP2116767A1 | 2009-11-11 | Carroni, Richard; Poyyapakkam, Madhavan Narasimhan; Bialkowski, Michal Tadeusz; Willets, Mark |
The present invention relates to a burner (1) for a combustion chamber of a gas turbine plant, with a lance (10) for introducing gaseous fuel into the burner (1). A shaft (11) of the lance (10) has at least one nozzle (14) for introducing gaseous fuel into the burner (1). A main injection direction (16) of the respective nozzle (14) is oriented onto a portion (18) of a burner wall (2). An introduction device (21) for a diverting fluid is provided, which is designed for introducing a diverting fluid counteracting an impingement of the fuel flow on the burner wall (2).
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| 39 | Chambre de combustion munie d'un fond générateur de prémélange | EP93400906.9 | 1993-04-07 | EP0565441A1 | 1993-10-13 | Ansart, Denis Roger Henri; Desaulty, Michel André Albert; Sandelis, Denis Jean Maurice |
L'invention est relative à une chambre de combustion pour turbo-machine, dont le fond permet une prévaporisation du carburant. A cet effet, selon l'invention, le fond comprend au moins deux profilés (5), en V, orientés vers l'amont (10) par rapport à l'enceinte de combustion (7), cependant qu'un premier passage(20) est ménagé entre les extrémités (16) des branches adjacentes de deux profilés successifs (5) et qu'un injecteur de carburant (11-12-13) est contenu à l'intérieur d'un espace délimité par les arêtes (14) et par les extrémités (16) desdites branches adjacentes (5), les axes (12A, 13A) des orifices d'injection (12, 13) intersectant lesdites branches (5). Une application est la réalisation d'une turbo-machine ayant une émission réduite d'oxydes d'azote. |
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| 40 | ASYMMETRICAL AND OFFSET FLARE TIP FOR FLARE BURNERS | US15798301 | 2017-10-30 | US20180119950A1 | 2018-05-03 | Matthew A. Martin; Kurt E. Kraus; Christopher Ferguson; Stefano Bietto |
| A flare burner for burning combustible waste gases with a manifold, at least two arms, and a plurality of outlets disposed on the plurality of arms. The arms may be perpendicular to the manifold. The arms may also extend outwardly from the manifold. The arms may extend into annuli, to produce oppositely flowing exit gas. A curved dispersing surface may be disposed above the manifold. The arms may comprise a curvilinear shape, or include both a linear and a curvilinear portion. The arms are unequal in length and may curve in an opposite direction from each other. The outlets are configured and spaced such that flame is short relative to size of the flare burner. | ||||||
