EP1207350B1 - Combustor and method for operating the same - Google Patents
Combustor and method for operating the same Download PDFInfo
- Publication number
- EP1207350B1 EP1207350B1 EP01126841A EP01126841A EP1207350B1 EP 1207350 B1 EP1207350 B1 EP 1207350B1 EP 01126841 A EP01126841 A EP 01126841A EP 01126841 A EP01126841 A EP 01126841A EP 1207350 B1 EP1207350 B1 EP 1207350B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- combustion chamber
- mixing zone
- lance
- chamber according
- 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
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/62—Mixing devices; Mixing tubes
- F23D14/64—Mixing devices; Mixing tubes with injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Definitions
- a combustion chamber with auto-ignition From the Laid-open specification DE-A1-44 17 538 is known a combustion chamber with auto-ignition.
- fuel and supporting air are introduced into a hot gas stream through a fuel lance, where they are mixed and the mixture is burned in a downstream combustion zone.
- the fuel lance is located in a mixing zone and is centrally located there. It is dimensioned for about 10% of the total volume flow through the channel, wherein the fuel can be injected transversely or in the direction of the flow.
- the injected fuel is entrained in conjunction with a portion of support air through a plurality of radial openings of the upstream injected vertebrae and mixed with the mainstream.
- the injected fuel follows the helical course of the vortices and is evenly distributed downstream in the chamber. This reduces the risk of impact rays on the opposite channel wall and the formation of "hot spots", as is the case with an untwisted flow.
- the invention solves the problem of providing a combustion chamber and a method for operating this combustion chamber, with which it is possible to minimize the disturbance of the hot gas flow in the mixing zone of the combustion chamber. This should be done with less cooling of the fuel lance and it should be an improved behavior of the combustion chamber in all load ranges.
- this is achieved in a device according to the preamble of claim 1, characterized in that the fuel is injected from at least one side wall of the mixing zone of the combustion chamber wherein the fuel lance has the shape of a ball or an ellipsoid and protrudes into the interior of the mixing zone and it is at
- the method according to claim 8 achieved in that the at least one fuel lance is embedded in a side wall of the mixing zone of the combustion chamber. wherein the fuel lance is in the form of a sphere or ellipsoid and projects into the interior of the mixing zone.
- support air is injected through this fuel lance.
- the at least one fuel lance has the shape of a ball or an ellipsoid extending in the main flow direction and is embedded in the side wall of the combustion chamber and protrudes into the interior of the mixing zone of the combustion chamber. Due to the design of the mixing zone as Venturi channel or possibly additionally existing internals (radially or in the circumferential direction), an increase of the speed and thus an improved mixing of hot gas and fuel / supporting air can be achieved. Trailing areas behind the fuel lance, in which fuel can accumulate, are practically excluded by this type of arrangement.
- the cooling of the fuel lance can be advantageously minimized.
- the area of the seal between the side wall of the mixing zone and fuel lance is also advantageously kept small and in an advantageous manner.
- An advantageous embodiment of the inventive method is that the fuel and the possibly existing supporting air are injected in different fuel / supporting air mixture jets in the mixing zone of the combustion chamber, wherein the different fuel / supporting air mixture jets in different directions or in different sectors are directed within the mixing zone of the combustion chamber.
- This embodiment is therefore particularly advantageous because depending on the utilization of the combustion chamber beams can be switched on or off.
- This is also advantageous in combination with the above-mentioned internals because of the targeted feeding of different sectors by the jets, the fuel can be transported at the same pressure in different areas within the mixing zone.
- the FIG. 1 shows an inventive combustion chamber 1, which is designed as a arranged around a shaft axis 9 annular combustion chamber.
- the combustion chamber 1 consists of a vortex generator 14, a mixing zone 11 and a combustion zone 12.
- Such ring burner chambers are very well suited to be operated as a self-igniting combustion chamber 1, the combustion chamber 1 then placed between two, not shown in the single figure turbines is.
- the upstream-acting turbine is designed only for partial expansion of the hot gases 5, the hot gases 5 then still flowing at a fairly high temperature into the vortex generator 14 and the mixing zone 11 of the combustion chamber 1.
- the temperature of auto-ignition is of course fuel-dependent.
- Between the mixing zone 11 and the combustion zone 12 is a abrupt cross-sectional widening 13. In the plane of the cross-sectional widening 13, the flame front sets in.
- the mixing zone 11, as in the FIG. 1 is shown, is designed as Venturi channel.
- another form of cross-sectional change may be chosen as long as this serves to improve acceleration and mixing of fuel 4 and hot gases 5.
- a fuel lance 2 In the area of the narrowest point is a fuel lance 2, with which fuel 3 and additional supporting air 4 are injected into the hot gases 5.
- the fuel lance 2 is embedded in a side wall 6 of the mixing zone 11. The distribution of the fuel 3 and the supporting air 2 thus takes place asymmetrically with respect to the cross section of the mixing zone 11.
- the fuel lance 2 represents only a slight disturbance of the flow, this disturbance being located only on the side wall 6 of the mixing zone 11 and no longer, as hitherto, centrally in the main flow.
- the fuel lance 2 in the form of a sphere or an ellipsoid extending in the main flow direction of the hot gas 5 is let into the side wall 6 of the combustion chamber 1 and protrudes into the interior of the mixing zone 11 of the combustion chamber 1 through a reduced area of the contact point between the fuel lance 2 and the hot gas flow can advantageously both the cooling of the fuel lance 2 minimized and the strength of the combustion chamber 1 can be increased overall.
- An advantageous embodiment of the inventive method is that the fuel 3 and the possibly existing supporting air 4 in various fuel / supporting air mixture jets 7 are injected into the mixing zone 11 of the combustion chamber 1, wherein the various fuel / supporting air mixture jets 7 are directed into different sectors or in different target areas within the mixing zone 11 of the combustion chamber 1.
- the FIG. 2 shows a section along the line II-II of FIG. 1 , There, the orientation of the beams 7 in different areas of the mixing zone 11 is clearly visible.
- the FIG. 3 further shows the section III of the FIG. 2 closer.
- the support air 4 surrounds the fuel 3 shell-shaped, the fuel jets are injected as a plain jet in the mixing zone.
- By choosing different ducts different types of fuel (gaseous / liquid) can be used.
- Such an injection principle is in principle from the Laid-Open Publication EP-A1-1, 030, 109 known.
- jets 7 are therefore particularly advantageous since, depending on the utilization of the combustion chamber, jets 7 can be switched on or off. This means that the rays 7 are individually spiked. Overall, the entire operating range can be increased from minimum to maximum fuel quantity. Thus, an improved partial load behavior is achieved, which has a positive effect in terms of pollutant behavior, ie formation of CO, NO x , UHC and so on. In addition, it is also possible to connect or disconnect all fuel / supporting air mixture jets 7 of a fuel lance 2 together.
- the inventive arrangement of the fuel lances 2 is also advantageous because trailing areas behind the fuel lance 2, in which fuel can accumulate 3, are virtually completely excluded.
- the mixing zone 11 By a change in cross section of the mixing zone 11, for example as Venturi channel or possibly additionally existing internals (radially or circumferentially) within the mixing zone 11 can increase the speed and thus an improved mixing of hot gas. 5 and fuel 3 / supporting air 4 can be achieved. This is also advantageous in combination with the internals mentioned, since with the targeted feeding of different sectors by the jets 7, the fuel 3 can be transported at the same pressure in different sectors.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Description
Bei der Erfindung handelt es sich um eine Brennkammer gemäss dem Oberbegriff des Anspruchs 1 bzw. um ein Verfahren zum Betrieb der Brennkammer gemäss Anspruch 8. Ein solches Verfahren und eine solche Vorrichtung sind aus Dokument
Aus der
Die Vorteile der zentralen Brennstoffeindüsung werden mit einer relativ schwierig zu kühlenden Brennstofflanzenoberfläche im Heissgasstrom erkauft. Zudem beeinflusst dieser Einbau die Strömung der Heissgase nicht unerheblich. Aus strömungstechnischen Gründen ist eine minimale Lanzenlänge erforderlich. Diese Lanzenlänge bedingt zudem, dass die Brennstofflanze zu Montagezwecken durch ein entsprechendes Langloch in den Brenner eingeführt wird. Dabei entsteht zwischen der Brennerwand und der Brennstofflanze ein relativ grosser Spalt, der relativ schwierig abzudichten ist. Entsprechend unregelmässige Luftleckagen beeinflussen das gesamte Verhalten des Brenners negativ.The advantages of the central fuel injection are obtained with a relatively difficult to cool fuel lance surface in the hot gas stream. In addition, this installation affects the flow of hot gases not insignificant. For aerodynamic reasons, a minimum lance length is required. This lance length also requires that the fuel lance is inserted for assembly purposes through a corresponding slot in the burner. This creates a relatively large gap between the burner wall and the fuel lance, which is relatively difficult to seal. Correspondingly irregular air leaks influence the overall behavior of the burner negatively.
Es ist Ziel dieser Erfindung, die genannten Nachteile zu vermeiden. Die Erfindung löst die Aufgabe, eine Brennkammer und ein Verfahren zum Betrieb dieser Brennkammer zu schaffen, mit welchem es möglich ist, die Störung der Heissgasströmung in der Mischzone der Brennkammer zu minimieren. Dies soll bei gleichzeitig geringerer Kühlung der Brennstofflanze geschehen und es soll ein verbessertes Verhalten der Brennkammer in allen Lastbereichen erreichen werden.It is an object of this invention to avoid the disadvantages mentioned. The invention solves the problem of providing a combustion chamber and a method for operating this combustion chamber, with which it is possible to minimize the disturbance of the hot gas flow in the mixing zone of the combustion chamber. This should be done with less cooling of the fuel lance and it should be an improved behavior of the combustion chamber in all load ranges.
Erfindungsgemäss wird dies bei einem Vorrichtung gemäss dem Oberbegriff des Anspruchs 1 dadurch erreicht, dass der Brennstoff von mindestens einer Seitenwand der Mischzone der Brennkammer eingedüst wird wobei die Brennstofflanze die Form einer Kugel oder eines Ellipsoiden hat und in den Inneraum der Mischzone ragt und es wird bei dem Verfahren gemäss Anspruch 8 dadurch erreicht, dass die mindestens eine Brennstofflanze in eine Seitenwand der Mischzone der Brennkammer eingelassen ist. wobei die Brennstofflanze die Form einer Kugel oder eines Ellipsoiden hat und in den Inneraum der Mischzone ragt. Selbstverständlich ist es denkbar, dass ebenfalls Stützluft durch diese Brennstofflanze eingedüst wird.According to the invention this is achieved in a device according to the preamble of
Ein Vorteil einer solchen seitlichen, asymmetrischen Eindüsung des Brennstoffs liegt insbesondere darin, dass durch die Brennstofflanze nur eine geringe Störung der Strömung verursacht wird, wobei sich diese Störung lediglich an der Seitenwand der Mischzone und nicht mehr zentral in der Hauptströmung befindet. Die mindestens eine Brennstofflanze hat die Form einer Kugel oder eines sich in Hauptströmungsrichtung erstreckenden Ellipsoiden und ist in die Seitenwand der Brennkammer eingelassen und ragt in den Innenraum der Mischzone der Brennkammer. Durch die Ausgestaltung der Mischzone als Venturikanal bzw. evtl. zusätzlich vorhandene Einbauten (radial oder in Umfangsrichtung) kann eine Erhöhung der Geschwindigkeit und damit eine verbesserte Vermischung von Heissgas und Brennstoff/Stützluft erreicht werden. Nachlaufgebiete hinter der Brennstofflanze, in welchen sich Brennstoff ansammeln kann, sind durch diese Art der Anordnung praktisch ausgeschlossen.An advantage of such lateral, asymmetrical injection of the fuel is, in particular, that only a small disturbance of the flow is caused by the fuel lance, whereby this disturbance is only on the side wall of the mixing zone and no longer centrally in the main flow. The at least one fuel lance has the shape of a ball or an ellipsoid extending in the main flow direction and is embedded in the side wall of the combustion chamber and protrudes into the interior of the mixing zone of the combustion chamber. Due to the design of the mixing zone as Venturi channel or possibly additionally existing internals (radially or in the circumferential direction), an increase of the speed and thus an improved mixing of hot gas and fuel / supporting air can be achieved. Trailing areas behind the fuel lance, in which fuel can accumulate, are practically excluded by this type of arrangement.
Durch eine verkleinerte Fläche der Kontaktstelle zwischen der Brennstofflanze und der Heissgasströmung kann die Kühlung der Brennstofflanze vorteilhaft minimiert werden. Der Bereich der Abdichtung zwischen Seitenwand der Mischzone und Brennstofflanze wird ebenfalls vorteilhaft klein und in vorteilhafter Form gehalten.By a reduced area of the contact point between the fuel lance and the hot gas flow, the cooling of the fuel lance can be advantageously minimized. The area of the seal between the side wall of the mixing zone and fuel lance is also advantageously kept small and in an advantageous manner.
Eine vorteilhafte Ausführungsform des erfindungsgemässen Verfahrens liegt darin, dass der Brennstoff und die eventuell vorhandene Stützluft in verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen in die Mischzone der Brennkammer eingedüst werden, wobei die verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen in verschiedene Richtungen bzw. in verschiedene Sektoren innerhalb der Mischzone der Brennkammer gerichtet sind. Diese Ausführungsform ist deshalb besonders vorteilhaft, da je nach Auslastung der Brennkammer Strahlen zu- oder abgeschaltet werden können. Dies ist auch in Kombination mit den oben erwähnten Einbauten deshalb vorteilhaft, da mit der gezielten Anspeisung von verschiedenen Sektoren durch die Strahlen, der Brennstoff bei gleichem Druck in verschiedene Bereiche innerhalb der Mischzone transportiert werden kann.An advantageous embodiment of the inventive method is that the fuel and the possibly existing supporting air are injected in different fuel / supporting air mixture jets in the mixing zone of the combustion chamber, wherein the different fuel / supporting air mixture jets in different directions or in different sectors are directed within the mixing zone of the combustion chamber. This embodiment is therefore particularly advantageous because depending on the utilization of the combustion chamber beams can be switched on or off. This is also advantageous in combination with the above-mentioned internals because of the targeted feeding of different sectors by the jets, the fuel can be transported at the same pressure in different areas within the mixing zone.
Die Erfindung wird anhand den beigefügten Figuren näher bezeichnet, wobei
- Fig. 1
- schematisch einen Schnitt durch eine Ringbrennkammer gemäss der Erfindung darstellt,
- Fig. 2
- einen Schnitt gemäss der Linie II-II in der
Figur 1 - Fig. 3
- den Ausschnitt III der
Figur 2
- Fig. 1
- schematically shows a section through an annular combustion chamber according to the invention,
- Fig. 2
- a section along the line II-II in the
FIG. 1 and - Fig. 3
- the section III of the
FIG. 2 ,
Es werden nur die für die Erfindung wesentlichen Elemente dargestellt. Gleiche Elemente werden in unterschiedlichen Figuren gleich bezeichnet.Only the elements essential to the invention are shown. Same elements are referred to the same in different figures.
Die
Die Mischzone 11, wie sie in der
Ein Vorteil einer solchen seitlichen, asymmetrischen Eindüsung des Brennstoffs 3 liegt insbesondere darin, dass die Brennstofflanze 2 nur eine geringe Störung der Strömung darstellt, wobei sich diese Störung lediglich an der Seitenwand 6 der Mischzone 11 und nicht mehr wie bisher zentral in der Hauptströmung befindet. Erfindungsgemäß ist die Brennstofflanze 2 in Form einer Kugel oder eines sich in Hauptströmungsrichtung des Heissgases 5 erstreckenden Ellipsoiden in die Seitenwand 6 der Brennkammer 1 eingelassen und ragt in den Innenraum der Mischzone 11 der Brennkammer 1. Durch eine verkleinerte Fläche der Kontaktstelle zwischen der Brennstofflanze 2 und der Heissgasströmung kann sowohl die Kühlung der Brennstofflanze 2 vorteilhaft minimiert als auch die Festigkeit der Brennkammer 1 insgesamt erhöht werden. In der Praxis bedeutet dies, dass die verkleinerte Oberfläche der Brennstofflanze 2 einfach zu kühlen ist. Eine verbesserte Abdichtung zur Vermeidung von Leckagen wird dadurch erreicht, dass der Durchbruch anstelle eines bisher bekannten Langlochs entsprechend kleiner, d.h. kreisrund oder ellipsenförmig, ausgeführt werden kann, was insgesamt eine Reduktion der Leckagemenge bedeutet.An advantage of such lateral, asymmetric injection of the
Eine vorteilhafte Ausführungsform des erfindungsgemässen Verfahrens liegt darin, dass der Brennstoff 3 und die eventuell vorhandene Stützluft 4 in verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen 7 in die Mischzone 11 der Brennkammer 1 eingedüst werden, wobei die verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen 7 in verschiedene Sektoren bzw. in verschiedene Zielräume innerhalb der Mischzone 11 der Brennkammer 1 gerichtet sind. Die
Der Einsatz von unterschiedlichen Düsengeometrien ist für diesen Zweck geeignet. Die Ausführungsform der Strahlen 7 ist deshalb besonders vorteilhaft, da je nach Auslastung der Brennkammer Strahlen 7 zu- oder abgeschaltet werden können. Dies bedeutet, dass die Strahlen 7 einzeln angespiesen werden. Insgesamt kann der gesamte Betriebsbereich von minimaler zu maximaler Brennstoffmenge vergrössert werden. Somit wird ein verbessertes Teillastverhalten erreicht, was sich in bezug auf Schadstoffverhalten, also Bildung von CO, NOx, UHC u.s.w. positiv auswirkt. Daneben ist es ebenso möglich, alle Brennstoff/Stützluft-Gemisch-Strahlen 7 einer Brennstofflanze 2 gemeinsam zu- oder abzuschalten.The use of different nozzle geometries is suitable for this purpose. The embodiment of the
Die erfindungsgemässe Anordnung der Brennstofflanzen 2 ist auch deshalb vorteilhaft, da Nachlaufgebiete hinter der Brennstofflanze 2, in welchen sich Brennstoff 3 ansammeln kann, praktisch vollständig ausgeschlossen sind.The inventive arrangement of the fuel lances 2 is also advantageous because trailing areas behind the
Durch eine Querschnittsänderung der Mischzone 11 beispielsweise als Venturikanal bzw. evtl. zusätzlich vorhandene Einbauten (radial oder in Umfangsrichtung) innerhalb der Mischzone 11 kann eine Erhöhung der Geschwindigkeit und damit eine verbesserte Vermischung von Heissgas 5 und Brennstoff 3 / Stützluft 4 erreicht werden. Dies ist auch in Kombination mit den erwähnten Einbauten deshalb vorteilhaft, da mit der gezielten Anspeisung von verschiedenen Sektoren durch die Strahlen 7, der Brennstoff 3 bei gleichem Druck in verschiedene Sektoren transportiert werden kann.By a change in cross section of the mixing
- 11
- Brennkammercombustion chamber
- 22
- Brennstofflanzefuel lance
- 33
- Brennstofffuel
- 44
- Stützluftsupport air
- 55
- HeissgasstromHot gas flow
- 66
-
Seitenwand des Brenners 1Side wall of the
burner 1 - 77
- Brennstoff/Luft-Gemisch-StrahlFuel / air mixture jet
- 88th
- Abdichtungseal
- 99
- Wellenachseshaft axis
- 1010
- Abgaseexhaust
- 1111
- Mischzonemixing zone
- 1212
- Verbrennungszonecombustion zone
- 1313
- QuerschnittserweiterungCross-sectional widening
- 1414
- Wirbelerzeugervortex generators
Claims (9)
- Combustion chamber consisting essentially of a mixing zone (11) and of a following combustion zone (12), the mixing zone (11) having at least one fuel lance (2) which can be operated by means of a fuel (3) and a supporting air (4), the fuel lance (2) being embedded into a side wall (6) of the mixing zone (11), characterized in that the fuel lance is in the form of a sphere or of an ellipsoid and projects into the inner space of the mixing zone (11).
- Combustion chamber according to Claim 1, characterized in that a vortex generator (14) is arranged upstream of the mixing zone (11).
- Combustion chamber according to Claim 1, characterized in that the fuel lance (2) has various orifices (7) for injecting a fuel/supporting-air mixture, and in that the orifices (7) are pointed in various directions inside the mixing zone (11).
- Combustion chamber according to Claim 1, characterized in that a seal (8) is located between the fuel lance (2) and the sidewall (6).
- Combustion chamber according to one of Claims 1-4, characterized in that the combustion chamber (1) is designed as an annular combustion chamber.
- Combustion chamber according to one of Claims 1-5, characterized in that a cross-sectional widening (13) is present between the mixing zone (11) and combustion zone (12).
- Combustion chamber according to one of Claims 1-6, characterized in that the mixing zone (11) is designed as a venturi duct.
- Method for operating a combustion chamber according to one of Claims 1-7, characterized in that the combustion of the fuel/supporting-air mixture takes place by means of autoignition.
- Method according to Claim 8, characterized in that the orifices (7) for injecting the fuel/supporting-air mixture are connected and disconnected as function of the load behaviour of the combustion chamber.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10056243 | 2000-11-14 | ||
| DE10056243A DE10056243A1 (en) | 2000-11-14 | 2000-11-14 | Combustion chamber and method for operating this combustion chamber |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1207350A2 EP1207350A2 (en) | 2002-05-22 |
| EP1207350A3 EP1207350A3 (en) | 2002-07-24 |
| EP1207350B1 true EP1207350B1 (en) | 2008-08-06 |
Family
ID=7663158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01126841A Expired - Lifetime EP1207350B1 (en) | 2000-11-14 | 2001-11-12 | Combustor and method for operating the same |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US6688111B2 (en) |
| EP (1) | EP1207350B1 (en) |
| JP (1) | JP2002162037A (en) |
| DE (2) | DE10056243A1 (en) |
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| EP1394471A1 (en) | 2002-09-02 | 2004-03-03 | Siemens Aktiengesellschaft | Burner |
| ES2309128T3 (en) * | 2002-09-20 | 2008-12-16 | Siemens Aktiengesellschaft | PRE-MIXED BURNER WITH PROFILED AIR MASS CURRENT, GAS TURBINE AND PROCEDURE FOR BURNING FUEL IN AIR. |
| DE10340826A1 (en) | 2003-09-04 | 2005-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Homogeneous mixture formation by twisted injection of the fuel |
| DE10348604A1 (en) * | 2003-10-20 | 2005-07-28 | Rolls-Royce Deutschland Ltd & Co Kg | Fuel injector with filmy fuel placement |
| WO2005095863A1 (en) * | 2004-03-31 | 2005-10-13 | Alstom Technology Ltd | Burner |
| CN101243287B (en) * | 2004-12-23 | 2013-03-27 | 阿尔斯托姆科技有限公司 | Premix burner with mixing section |
| DE102006051286A1 (en) * | 2006-10-26 | 2008-04-30 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Combustion device, has combustion chamber with combustion space and air injecting device including multiple nozzles arranged on circular line, where nozzles have openings formed as slotted holes in combustion space |
| NO326633B1 (en) * | 2006-12-28 | 2009-01-26 | Age Jorgen Skomsvold | Method and apparatus for engine and compression process |
| DE102007043626A1 (en) * | 2007-09-13 | 2009-03-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity |
| EP2260238B1 (en) * | 2008-03-07 | 2015-12-23 | Alstom Technology Ltd | Method of operating a premix burner |
| EP2116767B1 (en) * | 2008-05-09 | 2015-11-18 | Alstom Technology Ltd | Burner with lance |
| EP2211110B1 (en) * | 2009-01-23 | 2019-05-01 | Ansaldo Energia Switzerland AG | Burner for a gas turbine |
| US8667800B2 (en) * | 2009-05-13 | 2014-03-11 | Delavan Inc. | Flameless combustion systems for gas turbine engines |
| EP2420731B1 (en) * | 2010-08-16 | 2014-03-05 | Alstom Technology Ltd | Reheat burner |
| JP6138231B2 (en) * | 2012-03-23 | 2017-05-31 | ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ | Combustion device |
| US9677766B2 (en) | 2012-11-28 | 2017-06-13 | General Electric Company | Fuel nozzle for use in a turbine engine and method of assembly |
| US9599343B2 (en) | 2012-11-28 | 2017-03-21 | General Electric Company | Fuel nozzle for use in a turbine engine and method of assembly |
| ES2923690T3 (en) | 2014-12-02 | 2022-09-29 | Carrier Corp | Access control system with transfer of automatic mobile accreditation service |
| WO2016089832A1 (en) | 2014-12-02 | 2016-06-09 | Carrier Corporation | Access control system with virtual card data |
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| CN115899763B (en) * | 2022-11-30 | 2024-10-29 | 南京航空航天大学 | Tail edge shearing strengthening flame stabilizer of stress application or stamping combustion chamber |
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|---|---|---|---|---|
| GB2012415B (en) * | 1978-01-04 | 1982-03-03 | Secr Defence | Fuel mixers |
| US4420929A (en) * | 1979-01-12 | 1983-12-20 | General Electric Company | Dual stage-dual mode low emission gas turbine combustion system |
| DE68923413T2 (en) * | 1988-09-07 | 1996-04-04 | Hitachi Ltd | Fuel-air premixing device for a gas turbine. |
| US5109671A (en) * | 1989-12-05 | 1992-05-05 | Allied-Signal Inc. | Combustion apparatus and method for a turbine engine |
| US5097666A (en) * | 1989-12-11 | 1992-03-24 | Sundstrand Corporation | Combustor fuel injection system |
| EP0577862B1 (en) * | 1992-07-03 | 1997-03-12 | Abb Research Ltd. | Afterburner |
| CH687269A5 (en) * | 1993-04-08 | 1996-10-31 | Abb Management Ag | Gas turbine group. |
| DE4316474A1 (en) * | 1993-05-17 | 1994-11-24 | Abb Management Ag | Premix burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or a combustion system |
| GB9321505D0 (en) * | 1993-10-19 | 1993-12-08 | Europ Gas Turbines Ltd | Fuel injector |
| DE4408256A1 (en) * | 1994-03-11 | 1995-09-14 | Abb Management Ag | Method and device for flame stabilization of premix burners |
| DE4417538A1 (en) * | 1994-05-19 | 1995-11-23 | Abb Management Ag | Combustion chamber with self-ignition |
| DE4426351B4 (en) * | 1994-07-25 | 2006-04-06 | Alstom | Combustion chamber for a gas turbine |
| DE19510743A1 (en) * | 1995-02-20 | 1996-09-26 | Abb Management Ag | Combustion chamber with two stage combustion |
| DE19527453B4 (en) * | 1995-07-27 | 2009-05-07 | Alstom | premix |
| DE19651882A1 (en) * | 1996-12-13 | 1998-06-18 | Asea Brown Boveri | Method for frequency support when operating a power plant |
| AU7357298A (en) * | 1997-03-26 | 1998-10-20 | San Diego State University Foundation | Fuel/air mixing device for jet engines |
| US5850732A (en) * | 1997-05-13 | 1998-12-22 | Capstone Turbine Corporation | Low emissions combustion system for a gas turbine engine |
| ATE232282T1 (en) * | 1997-11-25 | 2003-02-15 | Alstom | BURNER FOR OPERATING A HEAT GENERATOR |
| DE19859829A1 (en) * | 1998-12-23 | 2000-06-29 | Abb Alstom Power Ch Ag | Burner for operating a heat generator |
| DE19905996A1 (en) | 1999-02-15 | 2000-08-17 | Abb Alstom Power Ch Ag | Fuel lance for injecting liquid and / or gaseous fuels into a combustion chamber |
-
2000
- 2000-11-14 DE DE10056243A patent/DE10056243A1/en not_active Ceased
-
2001
- 2001-11-12 DE DE50114185T patent/DE50114185D1/en not_active Expired - Lifetime
- 2001-11-12 EP EP01126841A patent/EP1207350B1/en not_active Expired - Lifetime
- 2001-11-13 US US09/987,117 patent/US6688111B2/en not_active Expired - Lifetime
- 2001-11-14 JP JP2001349121A patent/JP2002162037A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| EP1207350A3 (en) | 2002-07-24 |
| US6688111B2 (en) | 2004-02-10 |
| DE50114185D1 (en) | 2008-09-18 |
| DE10056243A1 (en) | 2002-05-23 |
| US20030093997A1 (en) | 2003-05-22 |
| JP2002162037A (en) | 2002-06-07 |
| EP1207350A2 (en) | 2002-05-22 |
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