EP0910776B1 - Burner with atomiser nozzle - Google Patents
Burner with atomiser nozzle Download PDFInfo
- Publication number
- EP0910776B1 EP0910776B1 EP97936627A EP97936627A EP0910776B1 EP 0910776 B1 EP0910776 B1 EP 0910776B1 EP 97936627 A EP97936627 A EP 97936627A EP 97936627 A EP97936627 A EP 97936627A EP 0910776 B1 EP0910776 B1 EP 0910776B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flow
- atomiser
- burner
- component
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers
Definitions
- the invention relates to a burner for combustion chambers of gas turbines according to the Preamble of claim 1.
- a burner is in the German patent application P 44 44 961.
- the reduction of pollutants in the combustion of kerosene in combustion chambers of aircraft engines is a constant development goal.
- the pollutant-reduced combustion chamber is a starting point.
- components of the combustion chamber be optimized. For example, it applies to fuel in all operating areas atomize as finely as possible and mix with the combustion air.
- This fuel preparation is used in the combustion chambers of modern aircraft gas turbines Air atomizing nozzles accomplished. The fuel flows according to their operating principle on a cylindrical surface to the end where due to air shear forces atomization begins.
- the mass flow of the secondary air flow must be greater than that of the primary airflow, so in the short distance from the end of the atomizer lip until it enters the combustion chamber, the peripheral pulse of the secondary air flow is not completely broken down and the formation of the recirculation vortex is endangered becomes. This in turn results in the distribution of the air-fuel ratio does not have the desired homogeneity at the nozzle outlet because the primary Airflow that is primarily involved in the mixing process is less than that secondary airflow is.
- An injection device for a combustion chamber is known from GB 2 272 756 A, which comprises an atomizer, several channels and a premixing section, the First of all, fuel to the guiding elements surrounding the channels with atomizer lips atomized and then in the premixing section with the air streams the channels that open into the premixing section are mixed.
- the premixing section is convergent-divergent to ensure good mixing of the atomized To ensure fuel with the air flows.
- GB 1 099 959 and GB 2 094 464 A describe a burner for solid or liquid Fuels disclosed in which the fuel mixes with multiple air streams is, whose channels through concentrically arranged pipes with divergent outlet nozzles be formed. When using liquid fuels, this is in one Pressure atomization at the point of entry into the nozzle area.
- the object of the invention is a generic burner specify a largely homogeneous distribution of the air-fuel mixture in the combustion chamber.
- the invention has the advantage that by twisting the two in the same direction Airflows considering mixing them before entering the combustion chamber to a high peripheral speed must not be avoided, so that too Dimensional current ratio can be selected regardless of the swirl of the currents can to make the distribution of the air-fuel mixture homogeneous. Regardless of a mixture of the two streams, the swirl number of the Air flow can be varied to a detached or a wall-to-wall Set the flow state in the combustion chamber. By positioning the atomizer lip narrowest flow cross-section in the atomizer nozzle or shortly before can atomize the fuel in a range of maximum air shear forces take place so that the atomization can take place optimally.
- the burner 1 shown in FIG. 1 is one of several arranged in a ring Burners of the combustion chamber 2 shown in sections of a not shown Aircraft gas turbine.
- the burner 1 has an atomizing nozzle 3 with a primary and a secondary Flow channel 4 or 5 and an injection nozzle 15.
- the two flow channels 4, 5 are in their channel course by ring or sleeve-shaped components 6, 7 determined and limited.
- the two concentric to the burner axis Z Flow channels 4, 5 each have a radial inlet section E. in order to then be deflected into a substantially axially extending outlet section A. to become.
- the sleeve-shaped component 6 separates the two channels 4, 5 from one another and has an annular atomizer lip in its downstream portion 8 with a conical taper.
- the component 6 On its upstream section the component 6 has a radially extending flange 9, the two axially spaced, annular inlet sections E of the channels 4.5 separates.
- the secondary flow channel running between the two components 6 and 7 5 is in its radially extending inlet section E of two parallel, annular wall sections of the two components 6 and 7 limited.
- the secondary flow channel 5 In the outlet section A, the secondary flow channel 5 is downstream radially outward from one, seen in the direction of flow, convergent-divergent running inner wall I of component 7 limited.
- the atomizer lip 8 ends immediately in front of the location with the narrowest flow cross section Q, which through the convergent-divergent course of the component 7 is defined so that downstream the atomizer lip 8, within the divergent section of the component 7 and downstream this results in a homogeneous mixing of the two air flows.
- the conically tapered inner wall of the atomizer lip 8 is by means of the injector 15 arranged in the primary flow channel 4 fine fuel sprayed in the form of a cone widening downstream like a fan, see above that it is deposited on the inner wall like a film.
- the same directional twist is responsible for the formation of the rotation vortex W the air flow in the flow channels 4 and 5, which in each case in the Entry sections E of the flow channels 4 and 5 arranged swirl devices 12 is generated.
- the cross sections of the two flow channels 4, 5 are dimensioned such that a mass flow ratio between primary and secondary air flow of is greater than 0.4. This ensures homogeneous mixing of the combustion chamber guaranteed with air-fuel mixture.
- the swirl formation in the same direction in the Flow channels 4 and 5 by varying the number of swirl in the two channels 4.5 a detached or wall-mounted combustion chamber flow can be represented, so that on location and formation of the rotary vortex W can be influenced.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Spray-Type Burners (AREA)
Abstract
Description
Die Erfindung betrifft einen Brenner für Brennkammern von Gasturbinen nach dem
Oberbegriff des Patentanspruches 1. Ein solcher Brenner ist in der deutschen Patentanmeldung
P 44 44 961 beschrieben.The invention relates to a burner for combustion chambers of gas turbines according to the
Preamble of
Die Reduktion von Schadstoffen, die bei der Verbrennung von Kerosin in Brennkammern von Flugtriebwerken entstehen, ist ein ständiges Entwicklungsziel. Hierbei ist die schadstoffreduzierte Brennkammer ein Ansatzpunkt. Für Verwirklichung der schadstoffreduzierten Verbrennungskonzepte müssen Komponenten der Brennkammer optimiert werden. So gilt es beispielsweise den Brennstoff in allen Betriebsbereichen möglichst fein zu zerstäuben und mit der Verbrennungsluft zu vermischen. Diese Brennstoffaufbereitung wird bei Brennkammern moderner Fluggasturbinen mit Luftzerstäuberdüsen bewerkstelligt. Nach deren Funktionsprinzip fließt der Brennstoff auf einer zylindrischen Oberfläche bis an dessen Ende, wo aufgrund der Luftscherkräfte die Zerstäubung einsetzt. Um örtlich unerwünschte Brennstoffanreicherungen im Brennraum der Brennkammer, die zur Rußbildung Anlaß geben könnten, zu vermeiden, wird die Luftströmung durch die Zerstäuberdüse in einen primären und sekundären Strömungskanal geteilt und gegensinnig verdrallt, so daß im Brennraum entgegengerichtete Rotationswirbel erzeugt werden. Hierzu ist jedem Strömungskanal eine radial angeströmte Drallvorrichtung zugeordnet. Eine hohe Drallzahl des Luftstromes führt zudem zu einem Rezirkulationswirbel an der rückseitigen Wand des Brennraumes wodurch eine homogene Verbrennung erzielt werden soll. Um eine vorzeitige Vermischung der beiden Luftströme zu vermeiden, die wiederum zu einer Reduktion der Umfangsgeschwindigkeit im sekundären Luftstrom führen würde, wird die Zerstäuberlippe, die den primären vom sekundären Luftstrom trennt, möglichst lang, bis an die brennraumseitige Mündung der Zerstäuberdüse ausgeführt. Bei konvergent-divergent ausgeführten Strömungskanälen hat dies allerdings zur Folge, daß die Zerstäubung sich nicht im Bereich der maximalen Luftscherkräfte abspielt und aus diesem Grund die Zerstäubung nicht das mögliche Optimum erreicht.The reduction of pollutants in the combustion of kerosene in combustion chambers of aircraft engines is a constant development goal. Here is the pollutant-reduced combustion chamber is a starting point. For realizing the Pollutant-reduced combustion concepts need components of the combustion chamber be optimized. For example, it applies to fuel in all operating areas atomize as finely as possible and mix with the combustion air. This fuel preparation is used in the combustion chambers of modern aircraft gas turbines Air atomizing nozzles accomplished. The fuel flows according to their operating principle on a cylindrical surface to the end where due to air shear forces atomization begins. To locally undesirable fuel enrichments in the combustion chamber of the combustion chamber, which could give rise to soot formation To avoid the airflow through the atomizer nozzle into a primary and secondary flow channel divided and twisted in opposite directions, so that in the combustion chamber opposite rotating vortices are generated. This is every flow channel assigned a swirl device with a radial flow. A high swirl number of the air flow also leads to a recirculation vortex on the back wall of the Combustion chamber whereby homogeneous combustion is to be achieved. To one to avoid premature mixing of the two air flows, which in turn becomes one Reduction of the peripheral speed in the secondary air flow would result the atomizer lip, which separates the primary from the secondary airflow, if possible long, to the mouth of the atomizer nozzle on the combustion chamber side. With convergent-divergent executed flow channels, however, this has the consequence that the atomization does not take place in the area of the maximum air shear forces for this reason the atomization does not reach the optimum possible.
Darüber hinaus muß der Massenstrom des sekundären Luftstroms größer als der des primären Luftstroms sein, damit in der kurzen Strecke vom Ende der Zerstäuberlippe bis zum Eintritt in den Brennraum der Umfangsimpuls des sekundären Luftstroms nicht vollständig abgebaut wird und die Entstehung des Rezirkulationswirbels gefährdet wird. Hieraus resultiert wiederum, daß die Verteilung des Luft- Brennstoffverhältnisses am Düsenaustritt nicht die gewünschte Homogenität aufweist, weil der primäre Luftstrom, der sich hauptsächlich am Mischungsprozeß beteiligt, geringer als der sekundäre Luftstrom ist.In addition, the mass flow of the secondary air flow must be greater than that of the primary airflow, so in the short distance from the end of the atomizer lip until it enters the combustion chamber, the peripheral pulse of the secondary air flow is not completely broken down and the formation of the recirculation vortex is endangered becomes. This in turn results in the distribution of the air-fuel ratio does not have the desired homogeneity at the nozzle outlet because the primary Airflow that is primarily involved in the mixing process is less than that secondary airflow is.
Aus der GB 2 272 756 A ist eine Einspritzvorrichtung für eine Brennkammer bekannt,
die einen Zerstäuber, mehrere Kanäle und eine Vormischstrecke umfaßt, wobei der
Brennstoff zunächst an die Kanäle umschließenden Leitelementen mit Zerstäuberlippen
zerstäubt und anschließend in der Vormischstrecke mit den Luftströmen aus
den Kanälen, die in die Vormischstrecke münden, vermischt wird. Die Vormischstrecke
ist konvergent-divergent ausgebildet, um eine gute Vermischung des zerstäubten
Brennstoffs mit den Luftströmen zu gewährleisten.An injection device for a combustion chamber is known from
In der GB 1 099 959 und der GB 2 094 464 A wird ein Brenner für feste oder flüssige
Brennstoffe offenbart, bei dem der Brennstoff mit mehreren Luftströmen vermischt
wird, deren Kanäle durch konzentrisch angeordnete Rohre mit divergenten Austrittsdüsen
gebildet werden. Beim Einsatz von flüssigen Brennstoffen wird dieser in einer
Druckzerstäubung an der Eintrittsstelle in den Düsenraum zerstäubt.
Hiervon ausgehend, ist es Aufgabe der Erfindung, einen gattungsgemäßen Brenner anzugeben, der eine weitgehend homogene Verteilung des Luftbrennstoffgemisches im Brennraum ermöglicht.Proceeding from this, the object of the invention is a generic burner specify a largely homogeneous distribution of the air-fuel mixture in the combustion chamber.
Die Aufgabe wird erfindungsgemäß durch die kennzeichnenden Merkmale des Patentanspruches
1 gelöst.The object is achieved by the characterizing features of the
Die Erfindung hat den Vorteil, daß durch die gleichsinnige Verdrallung der beiden Luftströme ein Vermischen derselben vor dem Eintritt in den Brennraum im Hinblick auf eine hohe Umfangsgeschwindigkeit nicht vermieden werden muß, so daß auch das Maßenstromverhältnis unabhängig von der Verdrallung der Ströme gewählt werden kann um die Verteilung des Luft- Brennstoffgemisches homogen gestalten zu können. Auch kann ohne Rücksicht auf eine Vermischung der beiden Ströme die Drallzahl der Luftströmung variiert werden, um einen abgelösten oder einen wandanliegenden Strömungszustand im Brennraum einzustellen. Durch die Positionierung der Zerstäuberlippe am engsten Strömungsquerschnitt in der Zerstäuberdüse oder kurz davor kann die Zerstäubung des Brennstoffes in einem Bereich der maximalen Luftscherkräfte erfolgen, so daß die Zerstäubung optimal erfolgen kann.The invention has the advantage that by twisting the two in the same direction Airflows considering mixing them before entering the combustion chamber to a high peripheral speed must not be avoided, so that too Dimensional current ratio can be selected regardless of the swirl of the currents can to make the distribution of the air-fuel mixture homogeneous. Regardless of a mixture of the two streams, the swirl number of the Air flow can be varied to a detached or a wall-to-wall Set the flow state in the combustion chamber. By positioning the atomizer lip narrowest flow cross-section in the atomizer nozzle or shortly before can atomize the fuel in a range of maximum air shear forces take place so that the atomization can take place optimally.
Weitere vorteilhafte Ausführungsformen der Erfindung ergeben sich aus den Patentansprüchen
2 bis 5.Further advantageous embodiments of the invention result from the
Eine bevorzugte Ausführungsform der Erfindung wird nachfolgend unter Bezugnahme auf die beigefügte Zeichnung erläutert. Es zeigt:
- Fig. 1
- einen Halbschnitt eines vorderen Brennkammerabschnittes mit Brenner,
- Fig. 2a
- im Halbschnitt den Strömungszustand in der Brennkammer und in der Zerstäuberdüse mit abgelöster Strömung
- Fig. 2b
- im Halbschnitt den Strömungszustand in der Brennkammer und in der Zerstäuberdüse mit wandanlieger Strömung.
- Fig. 1
- a half section of a front combustion chamber section with burner,
- Fig. 2a
- in half section the flow state in the combustion chamber and in the atomizer nozzle with detached flow
- Fig. 2b
- in half section the flow state in the combustion chamber and in the atomizer nozzle with flow against the wall.
Der in Fig. 1 gezeigte Brenner 1 ist einer von mehreren ringförmig angeordneten
Brennern der abschnittsweise dargestellten Brennkammer 2 einer nicht weiter dargestellten
Fluggasturbine. The
Der Brenner 1 weist eine Zerstäuberdüse 3 mit einem primären und einem sekundären
Strömungskanal 4 bzw. 5 sowie eine Einspritzdüse 15 auf. Die beiden Strömungskanäle
4, 5 werden durch ring- oder hülsenförmige Bauteile 6, 7 in ihrem Kanalverlauf
bestimmt und begrenzt. Die beiden konzentrisch zur Brennerachse Z geführten
Strömungskanäle 4, 5 weisen jeweils einen radialen verlaufenden Eintrittsabschnitt E
auf, um dann in einen im wesentlichen axial verlaufenden Austrittsabschnitt A umgelenkt
zu werden. Das hülsenförmige Bauteil 6 trennt die beiden Kanäle 4,5 voneinander
und weist in seinem stromabwärtigen Abschnitt eine ringförmige Zerstäuberlippe
8 mit konisch verjüngendem Verlauf auf. An seinem stromaufwärtigen Abschnitt
weist das Bauteil 6 einen radial sich erstreckenden Flansch 9 auf, der die beiden
axial voneinander beabstandeten, ringförmigen Eintrittsabschnitte E der Kanäle
4,5 trennt. Der zwischen den beiden Bauteilen 6 und 7 verlaufende sekundäre Strömungskanal
5 wird in seinem radial sich erstreckenden Eintrittsabschnitt E von zwei
parallel zueinander verlaufenden, ringförmigen Wandabschnitten der beiden Bauteile
6 und 7 begrenzt. Im Austrittsabschnitt A wird der sekundäre Strömungskanal 5 nach
radial außen hin von einer, in Strömungsrichtung gesehen, konvergent-divergent
verlaufende Innenwandung I des Bauteils 7 begrenzt. Die Zerstäuberlippe 8 endet
unmittelbar vor dem Ort mit dem engsten Strömungsquerschnitt Q, welcher durch den
konvergent-divergenten Verlauf des Bauteils 7 definiert wird, so daß stromabwärts
der Zerstäuberlippe 8, inerhalb des divergenten Abschnitts des Bauteils 7 und stromabwärts
hiervon eine homogene Vermischung der beiden Luftströme erfolgt.The
Auf die konisch verjüngt verlaufende Innenwandung der Zerstäuberlippe 8 wird mittels
der im primären Strömungskanal 4 angeordneten Einspritzdüse 15 Brennstoff fein
zerstäubt in Form eines sich stromab fächerartig aufweitenden Kegels aufgespritzt, so
daß sich dieser filmartig an der Innenwandung ablagert. An der stromabwärtigen
scharfkantigen Endkante 10 der Zerstäuberlippe 8 reißt der Brennstoffilm im Wege
einer ausgebildeten Scherströmung ab, so daß in den im Brennraum 11 der Brennkammer
2 sich ausbildenden Rotationswirbel W der Brennstoff nebelartig und teilweise
dampfförmig sowie gleichmäßig verteilt eingebracht wird. The conically tapered inner wall of the
Verantwortlich für die Ausbildung des Rotationswirbels W ist der gleichsinnige Drall
der Luftströmung in den Strömungskanälen 4 und 5, welcher durch jeweils in den
Eintrittsabschnitten E der Strömungskanäle 4 und 5 angeordnete Drallvorrichtungen
12 erzeugt wird.The same directional twist is responsible for the formation of the rotation vortex W
the air flow in the
Die beiden Strömungskanäle 4,5 sind in ihren Querschnitten derart dimensioniert, daß
sich ein Massenstromverhältnis zwischen primärer und sekundärer Luftströmung von
größer als 0,4 ergibt. Hierdurch wird eine homogene Vermischung des Brennraumes
mit Luft-Brennstoffgemisch gewährleistet.The cross sections of the two
Wie in den Fig. 2a und 2b zu sehen ist, ist durch die gleichsinnige Drallbildung in den
Strömungskanälen 4 und 5 durch Variation der Drallzahl in den beiden Kanälen 4,5
eine abgelöste bzw. wandanliegende Brennraumströmung darstellbar, so daß auf Lage
und Ausbildung des Rotationswirbels W Einfluß genommen werden kann. Bei der
wandanliegenden Strömung gemäß Fig. 2b mündet die Luftströmung stromabwärts
des divergenten Abschnitts des Bauteils 7 in den Brennraum und strömt parallel zur
radial verlaufenden Rückwand 13 des Brennraumes 11 ab, um dann in einem Rezirkulationswirbel
W etwa parallel zur Brennerachse Z zentral in Richtung des Brenners 1
zu strömen.As can be seen in FIGS. 2a and 2b, the swirl formation in the same direction in the
Bei der in Fig. 2a gezeigten Strömung hingegen sind zwei Rezirkulationswirbel W zu
erkennen, wobei sich der eine im Bereich der Rückwand 13 ausbildet und der andere
sich mit entgegengesetzter Drallrichtung im zentralen Bereich des Brennraumes 11
ausbildet.In contrast, in the flow shown in FIG. 2a, two recirculation vortices W are closed
recognize, one being formed in the area of the
Claims (5)
- A burner for combustors (2) in gas turbines with an atomiser nozzle (3) for atomising fuel in the combustion air which flows through a primary and a secondary flow channel (4, 5) upstream of the combustion chamber (11) of the combustor (2), the fuel being sprayed onto a wall in the atomising nozzle (3) and the flow chambers (4, 5) which discharge into the combustion chamber (11) being separated from a first component (6) which is positioned concentrically in relation to the burner axis A and has an atomiser lip which tapers in a sleeve shape, cylindrically or conically, and the outer, secondary flow channel (5) being radially externally delimited by a concentrically positioned annular second component (7) with an internal wall which runs convergently-divergently, characterised in that the second component (7) forms a place (Q) in the atomiser nozzle (3) with the narrowest flow cross section at the same axial level as or upstream of which the radially internally positioned first component (6) ends in the atomiser lip (8) and the flow of air (L) flows through the flow channels (4, 5) with a twist in the same direction.
- A burner according to Claim 1 characterised in that both components (6, 7) are positioned concentrically in relation to the burner axis (A) and between them form the annular, secondary flow channel (5).
- A burner according to Claim 1 or 2 characterised in that twist devices (12) are positioned before the outlet sections of the flow channels (4, 5).
- A burner according to one or more of the preceding claims characterised in that the flow channels (4, 5) are designed in such a way that the mass flow ratio of the primary to the secondary air flow is greater than 0.4.
- A burner according to one of the preceding claims characterised in that the burner (1) has an injection nozzle (15) via which fuel is injected into the primary flow channel (4) onto the internal wall (14) of the first component (6) upstream of the atomiser lip (8).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19627760 | 1996-07-10 | ||
| DE19627760A DE19627760C2 (en) | 1996-07-10 | 1996-07-10 | Burner with atomizer nozzle |
| PCT/EP1997/003595 WO1998001706A1 (en) | 1996-07-10 | 1997-07-08 | Burner with atomiser nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0910776A1 EP0910776A1 (en) | 1999-04-28 |
| EP0910776B1 true EP0910776B1 (en) | 2001-08-22 |
Family
ID=7799420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97936627A Expired - Lifetime EP0910776B1 (en) | 1996-07-10 | 1997-07-08 | Burner with atomiser nozzle |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US6244051B1 (en) |
| EP (1) | EP0910776B1 (en) |
| DE (2) | DE19627760C2 (en) |
| ES (1) | ES2162683T3 (en) |
| WO (1) | WO1998001706A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1340940A1 (en) | 2002-02-21 | 2003-09-03 | J. Eberspächer GmbH & Co. KG | Atomizing nozzle for a burner, especially for a heating apparatus used in an automobile |
| EP1342950A2 (en) | 2002-02-11 | 2003-09-10 | J. Eberspächer GmbH & Co. KG | Atomizing nozzle for a burner |
| DE10211590B4 (en) * | 2002-03-15 | 2007-11-08 | J. Eberspächer GmbH & Co. KG | Atomiser nozzle, in particular for a vehicle heater |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19803879C1 (en) | 1998-01-31 | 1999-08-26 | Mtu Muenchen Gmbh | Dual fuel burner |
| KR100375051B1 (en) * | 2000-01-25 | 2003-03-08 | (주) 젠터닷컴 | System and the method for real-time home shopping, and storage media having program source thereof |
| DE102004002246A1 (en) * | 2004-01-15 | 2005-08-11 | J. Eberspächer GmbH & Co. KG | Device for producing an air / hydrocarbon mixture |
| DE102005022772A1 (en) * | 2005-05-12 | 2007-01-11 | Universität Karlsruhe | Burner with partial premixing and pre-evaporation of the liquid fuel |
| FR2903170B1 (en) * | 2006-06-29 | 2011-12-23 | Snecma | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
| GB2444737B (en) * | 2006-12-13 | 2009-03-04 | Siemens Ag | Improvements in or relating to burners for a gas turbine engine |
| US20130067923A1 (en) * | 2011-09-20 | 2013-03-21 | General Electric Company | Combustor and method for conditioning flow through a combustor |
| US9423137B2 (en) * | 2011-12-29 | 2016-08-23 | Rolls-Royce Corporation | Fuel injector with first and second converging fuel-air passages |
| EP3098514A1 (en) * | 2015-05-29 | 2016-11-30 | Siemens Aktiengesellschaft | Combustor arrangement |
| FR3057648B1 (en) * | 2016-10-18 | 2021-06-11 | Safran Helicopter Engines | TURBOMACHINE COMBUSTION CHAMBER POOR INJECTION SYSTEM |
| US12072099B2 (en) * | 2021-12-21 | 2024-08-27 | General Electric Company | Gas turbine fuel nozzle having a lip extending from the vanes of a swirler |
| EP4202305A1 (en) * | 2021-12-21 | 2023-06-28 | General Electric Company | Fuel nozzle and swirler |
| DE102022002113A1 (en) | 2022-06-13 | 2023-12-14 | Mercedes-Benz Group AG | Burner for a motor vehicle, method for operating such a burner and motor vehicle |
| US12007115B1 (en) | 2023-02-28 | 2024-06-11 | Rtx Corporation | High shear swirler for gas turbine engine |
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| GB1099959A (en) * | 1965-10-28 | 1968-01-17 | Janos Miklos Beer | Improvements in or relating to burners for pulverised coal or like solid fuel or for liquid or gaseous fuel |
| US4180974A (en) * | 1977-10-31 | 1980-01-01 | General Electric Company | Combustor dome sleeve |
| NL8200333A (en) | 1981-02-27 | 1982-09-16 | Westinghouse Electric Corp | COMBUSTION DEVICE FOR GAS TURBINE. |
| GB2150277B (en) * | 1983-11-26 | 1987-01-28 | Rolls Royce | Combustion apparatus for a gas turbine engine |
| US5285631A (en) | 1990-02-05 | 1994-02-15 | General Electric Company | Low NOx emission in gas turbine system |
| DE4220060C2 (en) * | 1992-06-19 | 1996-10-17 | Mtu Muenchen Gmbh | Device for actuating a swirl device of a burner for gas turbine engines that controls the throughput of combustion air |
| DE4228816C2 (en) * | 1992-08-29 | 1998-08-06 | Mtu Muenchen Gmbh | Burners for gas turbine engines |
| GB2272756B (en) * | 1992-11-24 | 1995-05-31 | Rolls Royce Plc | Fuel injection apparatus |
| GB9326367D0 (en) * | 1993-12-23 | 1994-02-23 | Rolls Royce Plc | Fuel injection apparatus |
| DE4444961A1 (en) * | 1994-12-16 | 1996-06-20 | Mtu Muenchen Gmbh | Device for cooling in particular the rear wall of the flame tube of a combustion chamber for gas turbine engines |
| US5623827A (en) * | 1995-01-26 | 1997-04-29 | General Electric Company | Regenerative cooled dome assembly for a gas turbine engine combustor |
| US5836163A (en) * | 1996-11-13 | 1998-11-17 | Solar Turbines Incorporated | Liquid pilot fuel injection method and apparatus for a gas turbine engine dual fuel injector |
-
1996
- 1996-07-10 DE DE19627760A patent/DE19627760C2/en not_active Expired - Fee Related
-
1997
- 1997-07-08 EP EP97936627A patent/EP0910776B1/en not_active Expired - Lifetime
- 1997-07-08 WO PCT/EP1997/003595 patent/WO1998001706A1/en active IP Right Grant
- 1997-07-08 ES ES97936627T patent/ES2162683T3/en not_active Expired - Lifetime
- 1997-07-08 DE DE59704382T patent/DE59704382D1/en not_active Expired - Lifetime
- 1997-07-08 US US09/214,833 patent/US6244051B1/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1342950A2 (en) | 2002-02-11 | 2003-09-10 | J. Eberspächer GmbH & Co. KG | Atomizing nozzle for a burner |
| US6883730B2 (en) | 2002-02-11 | 2005-04-26 | J. Eberspächer GmbH & Co. KG | Atomizing nozzle for a burner |
| DE10205573B4 (en) * | 2002-02-11 | 2005-10-06 | J. Eberspächer GmbH & Co. KG | Atomizing nozzle for a burner |
| EP1340940A1 (en) | 2002-02-21 | 2003-09-03 | J. Eberspächer GmbH & Co. KG | Atomizing nozzle for a burner, especially for a heating apparatus used in an automobile |
| US6764302B2 (en) | 2002-02-21 | 2004-07-20 | J. Eberspacher Gmbh & Co. Kg | Atomizing nozzle for a burner, especially for a heater that can be used on a vehicle |
| DE10207311B4 (en) * | 2002-02-21 | 2005-06-09 | J. Eberspächer GmbH & Co. KG | Atomiser nozzle for a burner, in particular for a heater which can be used on a vehicle |
| DE10211590B4 (en) * | 2002-03-15 | 2007-11-08 | J. Eberspächer GmbH & Co. KG | Atomiser nozzle, in particular for a vehicle heater |
Also Published As
| Publication number | Publication date |
|---|---|
| DE19627760C2 (en) | 2001-05-03 |
| ES2162683T3 (en) | 2002-01-01 |
| WO1998001706A1 (en) | 1998-01-15 |
| EP0910776A1 (en) | 1999-04-28 |
| DE59704382D1 (en) | 2001-09-27 |
| DE19627760A1 (en) | 1998-01-15 |
| US6244051B1 (en) | 2001-06-12 |
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