EP2954262B1 - Jet burner with cooling duct in the base plate - Google Patents

Jet burner with cooling duct in the base plate Download PDF

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Publication number
EP2954262B1
EP2954262B1 EP14705083.5A EP14705083A EP2954262B1 EP 2954262 B1 EP2954262 B1 EP 2954262B1 EP 14705083 A EP14705083 A EP 14705083A EP 2954262 B1 EP2954262 B1 EP 2954262B1
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EP
European Patent Office
Prior art keywords
base plate
burner
jet
jet burner
gas side
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.)
Active
Application number
EP14705083.5A
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German (de)
French (fr)
Other versions
EP2954262A1 (en
Inventor
Christian Beck
Simon Bez
Björn Buchholz
Thomas Grieb
Matthias Hase
Werner Krebs
Berthold Köstlin
Stefan Reich
Marc Tertilt
Jan Wilkes
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Siemens AG
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Siemens AG
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Publication date
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Publication of EP2954262A1 publication Critical patent/EP2954262A1/en
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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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/002—Wall structures
    • 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
    • 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
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the invention therefore relates to the cooling of the nozzle carrier of a jet burner.
  • Jet-stabilized combustion systems in which the fuel is burned in a jet flame downstream of the burner have a simple premixing zone compared to spin-stabilized systems. Since the pressure difference in the burner is converted exclusively into the axial velocity component, these burners are characterized by a low flashback tendency, which is why even highly reactive combustion mixtures with a higher hydrogen content can be burned with this burner.
  • jet-stabilized combustion systems which can cause flame instabilities.
  • a jet-stabilized combustion system discloses, for example, the US 2010/0300104 A1 .
  • nozzle carrier nozzle carrier
  • a jet burner is also off EP 2 187 125 A1 known.
  • the nozzle carrier is usually made of solid forged material, which is very expensive but advantageous for the prototype design because it is comparatively easy to manufacture. Furthermore, on the hot gas side of the nozzle carrier due to good mechanical properties and good heat transfer No cooling required between the air in the nozzle carrier and nozzle carrier.
  • the machining of the required holes is expensive, the construction is massive and thus the weight is high, also the component geometry is limited by the manufacturing method. As a result, results in a very expensive production for the component with partially unrealizable features. At least it is very expensive to introduce additional features or features, such as cooling or scavenging air channels in the nozzle carrier.
  • the object of the invention is to further develop said jet burner, so that manufacturing costs can be minimized and additional design features can be integrated, which positively influence the operation of the combustion system.
  • the cooling channel may be one of a plurality of cooling channels, or else a type of cavity which extends almost over the entire surface of the base plate and through which the cooling air flows.
  • Active cooling by, for example, effusion cooling adversely affects NOx emissions because the air mass flow to the flame front is reduced. This locally increases the flame temperature and thus the NOx emissions. This is avoided in that, according to the invention, the at least one cooling channel opens into a burner stage, as a result of which cooling air is no longer simply released into the combustion chamber.
  • the burner stage comprises a pilot burner arranged on the base plate. This can namely be operated at a lower pressure drop, as the jet nozzles of the main burner.
  • the air required for the operation of the pilot burner can be supplied from the cooling channel, i. if the pilot burner is supplied with the necessary air directly and exclusively via the cooling channel and a uniform air mass flow to the flame front is ensured.
  • thermo barrier coating thermal barrier coating
  • the at least one cooling channel can be acted upon by cooling air via an opening on a peripheral edge of the base plate.
  • the at least one cooling channel is via an opening At the cold gas side of the base plate can be acted upon with cooling air.
  • the at least one cooling channel can be acted upon by a cooling air line which is arranged in a wall surrounding the jet nozzles and adjoining the base plate, opening toward the cold gas side of the jet burner and opening into the base plate.
  • the cooling channel is designed as a type of cavity, dead water areas can form behind the premix passages that are flowed around by the cooling air. In these areas, the heat transfer or the cooling of the base plate is reduced by the cooling air. In order to avoid dead zones behind the jet nozzles or at least to minimize, elements for increased heat transfer or flow guidance can be introduced into the flow path.
  • the cooling channel in the base plate spoilers or vortex generators such as ribs or relatively small depressions (dimples) have.
  • At least the base plate is a casting.
  • the limitations imposed by the prior art forging process can be minimized by using a casting process to pattern the nozzle carrier.
  • the application of this process allows the production of a near-net shape blank, which has to be processed slightly to final contour.
  • holes can already be made in the casting process, saving volume and mass.
  • more complex geometries can be realized with the casting process.
  • additional functions can be introduced into the component and the component properties can thus be improved.
  • the flexibility of the component geometry made possible by the casting process could, if sufficient optimization of the cooling, reduce the operating temperature of the component to such an extent that, instead of a nickel-base alloy, a more favorable one Cast steel material can be used.
  • the component can be designed to suit stress.
  • the casting further comprises the jet nozzles, which form the main burner. These can be poured directly when casting the base plate.
  • the base plate is a sheet metal construction. Even with this solution, the manufacturing costs can be reduced alone because of significantly lower raw material costs compared to the version with solid blacksmith material.
  • the air supply of the pilot burner and the main burner are separated. This allows the pilot burner air mass flow to be used for cooling the burner.
  • Producing the cast jet burner of the present invention or using a sheet metal construction not only saves costs but also integrates additional design features into the nozzle carriers that positively affect the operation of the combustion system (e.g., improved life, greater recoil safety, and less pressure loss). These positive properties are achieved in the present invention by the introduction of cooling and Spippokanälen.
  • FIG. 1 schematically shows a section through a portion of a jet burner 1 in the longitudinal direction, ie along the central axis 2 of the burner 1 according to the prior art.
  • the burner 1 has at least one jet nozzle 4 arranged in a nozzle carrier 3.
  • the jet nozzle 4 comprises a jet nozzle inlet 5 and a jet nozzle outlet 6.
  • the jet nozzle outlet 6 is adjoined by the combustion chamber 7.
  • the jet nozzle 4 is arranged in the nozzle carrier 3, that the jet nozzle inlet 5 of the rear wall 8 of the burner 1 faces.
  • the combustion chamber 7 facing side of the jet burner 1 is referred to as hot gas side 9, the combustion chamber 7 side facing away from the cold gas side 10 is referred to.
  • a fuel nozzle 11 is arranged in the region of the jet nozzle inlet 5 of the jet nozzle 4. Through the fuel nozzle 11, fuel is injected into the jet nozzle 4.
  • the burner 1 further comprises a radially with respect to the central axis 2 of the burner 1 outer housing part 12 which forms an annular channel 13 with the nozzle carrier 3. Through this annular channel 13, air 14 flows from the compressor in the direction of the rear wall 8 of the burner 1 and is deflected there, so that it passes through the jet nozzle inlet 5 in the jet nozzles 4.
  • FIG. 1 does not show that burners, in particular premix burners such as the jet burner 1 shown, can be equipped with an additional pilot burner to ensure stable combustion over a wide operating range, in particular at idle and part load range.
  • a pilot burner is then typically arranged on the central axis 2 of the burner.
  • FIG. 2 schematically shows a section through a jet burner 1 perpendicular to a central axis 2 of the burner 1.
  • the nozzle carrier 3 has a circular cross-section.
  • a certain number of jet nozzles 4 is arranged substantially annular.
  • Each jet nozzle 4 has a circular cross section.
  • FIG. 3 schematically shows a section through a jet burner 101, wherein the section is perpendicular to the central axis of the burner 101.
  • the burner 101 also has a nozzle carrier 3, which has a circular cross-section and in which a number of inner and outer jet nozzles 4, 104 is arranged.
  • the jet nozzles 4, 104 each have a circular cross-section, wherein the outer jet nozzles 4 have an equal or larger cross-sectional area than the inner jet nozzles 104.
  • the outer jet nozzles 4 are arranged substantially annularly within the nozzle carrier 3 and form an outer ring.
  • the inner jet nozzles 104 are also arranged annularly within the housing 3.
  • the inner jet nozzles 104 form an inner ring which is concentric with the outer jet nozzle ring.
  • FIGS. 2 and 3 merely show examples of the arrangement of jet nozzles 4, 104 within a jet burner 1, 101.
  • the burner 1, 101 may include a pilot burner.
  • FIG. 4 shows a section through a portion of a jet burner 15 according to the invention, in which the jet nozzles 16 are arranged on a base plate 17, wherein the base plate 17 has cooling channels 18, which can be poured, for example, when using a casting process directly into the base plate 17 with.
  • the jet nozzles 16, which form the main burner (premix burner) can be cast directly.
  • the base plate 17 is cooled by the cooling air channels 18.
  • the base plate 17 can be supplemented by a thermal barrier coating 19 (thermal barrier coating).
  • thermal barrier coatings 19 thermal barrier coating
  • effective cooling it may be possible to dispense with, for example, nickel-based alloys.
  • a cost reduction is to be expected even when using a nickel-based alloy, since significantly less material is required for a cast component.
  • the cooling air 20 can be removed either from the annular channel 13 or from the plenum 21 in front of the base plate 17.
  • the cooling air 20 is supplied through openings 22 at a peripheral edge 23 of the base plate 17 to the cooling channel 18.
  • the cooling air 20 is supplied through openings 24 on the cold gas side 10 of the base plate 17 to the cooling channel 18.
  • the cooling air 20 does not enter directly into the combustion chamber 7, but is the pilot burner (see. FIG. 6 ).
  • a high pressure gradient is available here, which can be used to connect the cooling channels 18 with elements 26 for increased heat transfer (eg ribs or depressions 36) and / or Provide flow guide (eg baffles 35) (see. FIG. 7 ).
  • the cooling channels 18 must here be correspondingly large, so that the desired pilot air split, i. the proportion of air supplied to the pilot based on the total amount of air 14, is also achieved at the predetermined differential pressure.
  • the cooling channels 18 would be equipped with no or only a few ribs or similar elements 26. The necessary cooling effect is realized via the increased mass flow.
  • FIG. 5 shows another way of cooling air extraction.
  • the cooling air for the base plate 17 (or at least a portion of the cooling air) is removed from the boundary layer at the deflection 30 from the annular channel 13 into the plenum 21. This removal stabilizes the boundary layer and lasts longer. This results in a lower Umlenk horriner.
  • the obtained pressure can be used eg for a higher jet speed.
  • the cooling air 20 enters the cooling channel 18 of the base plate 17th
  • FIG. 6 shows a preferred embodiment of the cooling concept according to the invention, in which air flows through a cooling channel 18, wherein the cooling channel 18 extends in the manner of a cavity almost over the entire surface of the base plate 17 and wherein the cooling air 20, after having passed through the cooling channel 18, the pilot burner 33 is supplied as pilot air 27.
  • the air supply of the pilot burner 33 takes place here directly and exclusively via the cooling channel 18.
  • the over the cold gas side 10 of the base plate 17 also extending circumferential wall 34 approaches with increasing distance from the base plate 17 of a central axis 2 of the Jet burner 15 on.
  • This wall 34, and the surrounding, typically cylindrical outer housing part 12 then form a kind of diffuser, whereby the air flow 14 provided by the compressor slows down and the pressure increases advantageously.
  • FIG. 7 shows a section through a jet burner 15 according to the invention perpendicular to the central axis 2, which can be realized advantageously by means of a sheet metal construction, since the cooling channel 18 extends substantially over the base of the base plate 17, possibly only interrupted by supporting elements.
  • the cooling air 20 between hot gas 9 and cold gas side 10 of the base plate 17 is guided from radially outside to radially inside (the pilot burner is not shown). In this case, the cooling air 20 flowing inwards towards the pilot must flow around the jet nozzles 4 of the premix passages of the main burner 25.
  • elements 26 for increased heat transfer or flow guidance can be introduced into the flow path, such as FIG. 7 with the baffles 35 (spoilers) or depressions 36 (dimples) shows.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)

Description

In modernen Gasturbinenverbrennungssystemen übersteigen lokale Heißgastemperaturen bisweilen zulässige Temperaturgrenzen von Superlegierungen mit Wärmedämmschichten, weshalb zusätzliche Kühlung notwendig ist.In modern gas turbine combustion systems, local hot gas temperatures sometimes exceed allowable temperature limits of superalloys with thermal barrier coatings, therefore additional cooling is necessary.

Die Erfindung betrifft daher die Kühlung des Düsenträgers eines Strahlbrenners.The invention therefore relates to the cooling of the nozzle carrier of a jet burner.

Strahlstabilisierte Verbrennungssysteme bei denen stromab des Brenners der Brennstoff in einer Strahlflamme verbrannt wird, weisen im Vergleich zu drallstabilisierten Systemen eine einfache Vormischzone auf. Da die Druckdifferenz im Brenner ausschließlich in die Axialgeschwindigkeitskomponente gewandelt wird, zeichnen sich diese Brenner durch eine geringe Flammenrückschlagsneigung aus, weshalb auch höher reaktive Verbrennungsgemische mit höherem Wasserstoffanteil mit diesem Brenner verbrannt werden können.Jet-stabilized combustion systems in which the fuel is burned in a jet flame downstream of the burner have a simple premixing zone compared to spin-stabilized systems. Since the pressure difference in the burner is converted exclusively into the axial velocity component, these burners are characterized by a low flashback tendency, which is why even highly reactive combustion mixtures with a higher hydrogen content can be burned with this burner.

Weiterhin werden in strahlstabilsierten Verbrennungssystemen keine drallinduzierten Wirbelstrukturen erzeugt, die Flammeninstabilitäten verursachen können. Ein solches strahlstabilisiertes Verbrennungssystem offenbart beispielsweise die US 2010/0300104 A1 . Zur Aufnahme der Vormischpassagen wird ein sogenannter "Jet Carrier" (Düsenträger) benötigt, der je nach Bauart eine unterschiedliche Anzahl von Düsen aufweist, die konzentrisch auf einem oder mehreren Ringen angeordnet werden können. Ein Strahlbrenner ist ebenfalls aus EP 2 187 125 A1 bekannt.Furthermore, no spin-induced vortex structures are generated in jet-stabilized combustion systems, which can cause flame instabilities. Such a jet-stabilized combustion system discloses, for example, the US 2010/0300104 A1 , To accommodate the Vormischpassagen a so-called "jet carrier" (nozzle carrier) is required, which, depending on the design of a different number of nozzles, which can be arranged concentrically on one or more rings. A jet burner is also off EP 2 187 125 A1 known.

Der Düsenträger wird üblicherweise aus massivem Schmiedmaterial hergestellt, was sehr teuer, aber für das Prototyp-Design vorteilhaft ist, da er so vergleichsweise einfach herzustellen ist. Ferner wird auf der Heißgasseite des Düsenträgers aufgrund guter mechanischer Eigenschaften und gutem Wärmeübertrag zwischen Luft im Düsenträger und Düsenträger keine Kühlung benötigt.The nozzle carrier is usually made of solid forged material, which is very expensive but advantageous for the prototype design because it is comparatively easy to manufacture. Furthermore, on the hot gas side of the nozzle carrier due to good mechanical properties and good heat transfer No cooling required between the air in the nozzle carrier and nozzle carrier.

Aufgrund der aktuellen Fertigung des Düsenträgers durch Schmieden aus beispielsweise einer Nickellegierung ist die Bearbeitung der erforderlichen Bohrungen aufwendig, die Bauweise ist massiv und somit ist auch das Gewicht hoch, ferner ist die Bauteilgeometrie durch die Herstellmethode eingeschränkt. Infolgedessen ergibt sich eine sehr teure Fertigung für das Bauteil mit teilweise nicht realisierbaren Merkmalen. Zumindest ist es sehr aufwändig, zusätzliche Merkmale oder Besonderheiten, wie Kühl- oder Spülluftkanäle, in den Düsenträger einzubringen.Due to the current production of the nozzle carrier by forging from, for example, a nickel alloy, the machining of the required holes is expensive, the construction is massive and thus the weight is high, also the component geometry is limited by the manufacturing method. As a result, results in a very expensive production for the component with partially unrealizable features. At least it is very expensive to introduce additional features or features, such as cooling or scavenging air channels in the nozzle carrier.

Auch aufgrund der Kosten kommt eine Serienproduktion nicht in Betracht.Also due to the costs of a series production is not considered.

Aufgabe der Erfindung ist es, den genannten Strahlbrenner weiterzuentwickeln, so dass Herstellungskosten minimiert und zusätzliche Designmerkmale integriert werden können, die den Betrieb des Verbrennungssystems positiv beeinflussen.The object of the invention is to further develop said jet burner, so that manufacturing costs can be minimized and additional design features can be integrated, which positively influence the operation of the combustion system.

Erfindungsgemäß wird diese Aufgabe gelöst durch die Vorrichtung gemäß Anspruch 1. Vorteilhafte Weiterbildungen der Erfindung sind in den abhängigen Ansprüchen definiert. Indem bei einem Strahlbrenner mit einer im Betrieb einer Brennkammer zugewandten Heißgasseite und einer von der Brennkammer abgewandten Kaltgasseite, umfassend eine Grundplatte, auf der mehrere Strahldüsen angeordnet sind, wobei die Grundplatte mindestens einen Kühlkanal aufweist, der mindestens eine Kühlkanal in eine Brennerstufe mündet, die einen auf der Grundplatte angeordneten Pilotbrenner umfasst, wird erreicht, dass der bisherige Düsenträger deutlich kostengünstiger hergestellt werden kann, als bei massiver Bauweise.According to the invention this object is achieved by the device according to claim 1. Advantageous developments of the invention are defined in the dependent claims. In a jet burner with a hot gas side facing a combustion chamber and a cold gas side facing away from the combustion chamber, comprising a base plate on which a plurality of jet nozzles are arranged, wherein the base plate has at least one cooling channel, which opens at least one cooling channel in a burner stage, the one Includes arranged on the base plate pilot burner, it is achieved that the previous nozzle carrier can be made significantly cheaper than solid construction.

Erst durch aktive Kühlung kann ein kostengünstigeres Material für den Düsenträger verwendet werden, um die durch die leichtere Bauweise verloren gegangene mechanische Belastbarkeit zu kompensieren. Dabei kann der Kühlkanal einer von mehreren Kühlkanälen sein, oder aber auch eine Art Hohlraum, der sich nahezu über die gesamte Fläche der Grundplatte erstreckt und durch den die Kühlluft strömt.Only by active cooling a cheaper material for the nozzle carrier can be used to the lost by the lighter design mechanical strength compensate. In this case, the cooling channel may be one of a plurality of cooling channels, or else a type of cavity which extends almost over the entire surface of the base plate and through which the cooling air flows.

Die aktive Kühlung durch beispielsweise Effusionskühlung beeinflusst NOx-Emissionen negativ, da der Luftmassenstrom zur Flammenfront verringert ist. Dadurch erhöht sich lokal die Flammentemperatur und somit die NOx-Emissionen. Dies wird dadurch vermieden, dass nach der Erfindung der mindestens eine Kühlkanal in eine Brennerstufe mündet, wodurch Kühlluft nicht mehr einfach nur in die Brennkammer abgegeben wird.Active cooling by, for example, effusion cooling adversely affects NOx emissions because the air mass flow to the flame front is reduced. This locally increases the flame temperature and thus the NOx emissions. This is avoided in that, according to the invention, the at least one cooling channel opens into a burner stage, as a result of which cooling air is no longer simply released into the combustion chamber.

Nach der Erfindung umfasst die Brennerstufe einen auf der Grundplatte angeordneten Pilotbrenner. Dieser kann nämlich bei geringerem Druckverlust betrieben werden, als die Strahldüsen des Hauptbrenners.According to the invention, the burner stage comprises a pilot burner arranged on the base plate. This can namely be operated at a lower pressure drop, as the jet nozzles of the main burner.

Insbesondere ist es vorteilhaft, wenn die für den Betrieb des Pilotbrenners benötigte Luft aus dem Kühlkanal zuführbar ist, d.h. wenn der Pilotbrenner direkt und ausschließlich über den Kühlkanal mit der nötigen Luft versorgt wird und ein gleichmäßiger Luftmassenstrom zur Flammenfront sichergestellt ist.In particular, it is advantageous if the air required for the operation of the pilot burner can be supplied from the cooling channel, i. if the pilot burner is supplied with the necessary air directly and exclusively via the cooling channel and a uniform air mass flow to the flame front is ensured.

Es ist vorteilhaft, wenn die Grundplatte heißgasseitig eine Wärmedämmschicht (thermal barrier coating) aufweist, wodurch die Werkstofftemperatur im Betrieb des Brenners bzw. der Kühlbedarf gesenkt werden.It is advantageous if the base plate on the hot gas side, a thermal barrier coating (thermal barrier coating), whereby the material temperature in the operation of the burner or the cooling demand can be reduced.

In einer vorteilhaften Ausführungsform der Erfindung ist der mindestens eine Kühlkanal über eine Öffnung an einem umlaufenden Rand der Grundplatte mit Kühlluft beaufschlagbar.In an advantageous embodiment of the invention, the at least one cooling channel can be acted upon by cooling air via an opening on a peripheral edge of the base plate.

In einer alternativen vorteilhaften Ausführungsform der Erfindung ist der mindestens eine Kühlkanal über eine Öffnung an der Kaltgasseite der Grundplatte mit Kühlluft beaufschlagbar.In an alternative advantageous embodiment of the invention, the at least one cooling channel is via an opening At the cold gas side of the base plate can be acted upon with cooling air.

In einer weiteren vorteilhaften Ausführungsform der Erfindung ist der mindestens eine Kühlkanal über eine in einer die Strahldüsen umgebenden, an die Grundplatte anschließenden Wandung angeordnete, zur Kaltgasseite des Strahlbrenners hin geöffnete und in die Grundplatte mündende Kühlluftleitung beaufschlagbar.In a further advantageous embodiment of the invention, the at least one cooling channel can be acted upon by a cooling air line which is arranged in a wall surrounding the jet nozzles and adjoining the base plate, opening toward the cold gas side of the jet burner and opening into the base plate.

Ist der Kühlkanal als eine Art Hohlraum ausgeführt, können sich Totwasser-Bereiche hinter den von der Kühlluft umströmten Vormischpassagen ausbilden. In diesen Bereichen ist die Wärmeübertragung bzw. die Kühlung der Grundplatte durch die Kühlluft verringert. Um Totwassergebiete hinter den Strahldüsen zu vermeiden oder zumindest zu minimieren, können Elemente für erhöhte Wärmeübertragung bzw. Strömungsführung in den Strömungspfad eingebracht sein. Beispielsweise kann der Kühlkanal in der Grundplatte Umlenkbleche (spoilers) oder Wirbelerzeuger wie Rippen oder vergleichsweise kleine Vertiefungen (dimples) aufweisen.If the cooling channel is designed as a type of cavity, dead water areas can form behind the premix passages that are flowed around by the cooling air. In these areas, the heat transfer or the cooling of the base plate is reduced by the cooling air. In order to avoid dead zones behind the jet nozzles or at least to minimize, elements for increased heat transfer or flow guidance can be introduced into the flow path. For example, the cooling channel in the base plate spoilers or vortex generators such as ribs or relatively small depressions (dimples) have.

In einer vorteilhaften Ausführungsform ist zumindest die Grundplatte ein Gussteil. Die Einschränkungen, bedingt durch das Schmiede-Verfahren aus dem Stand der Technik, können durch Verwendung eines Gussprozesses zum Urformen des Düsenträgers minimiert werden. Die Anwendung dieses Prozesses erlaubt die Herstellung eines endkonturnahen Rohlings, der geringfügig auf Endkontur bearbeitet werden muss. Zum Beispiel können Bohrungen durch Verwendung von Kernen bereits im Gussprozess dargestellt werden, was Volumen und Masse einspart. Ferner können mit dem Gussverfahren komplexere Geometrien realisiert werden. Hierdurch können zusätzliche Funktionen ins Bauteil eingebracht werden und die Bauteileigenschaften damit verbessert werden. Die durch den Gussprozess ermöglichte Flexibilität der Bauteilgeometrie könnte bei genügender Optimierung der Kühlung die Betriebstemperatur des Bauteils soweit senken, dass anstelle einer Nickelbasis-Legierung ein günstigerer Stahlguss-Werkstoff verwendet werden kann. Ferner kann das Bauteil beanspruchungsgerecht ausgelegt werden.In an advantageous embodiment, at least the base plate is a casting. The limitations imposed by the prior art forging process can be minimized by using a casting process to pattern the nozzle carrier. The application of this process allows the production of a near-net shape blank, which has to be processed slightly to final contour. For example, through the use of cores, holes can already be made in the casting process, saving volume and mass. Furthermore, more complex geometries can be realized with the casting process. As a result, additional functions can be introduced into the component and the component properties can thus be improved. The flexibility of the component geometry made possible by the casting process could, if sufficient optimization of the cooling, reduce the operating temperature of the component to such an extent that, instead of a nickel-base alloy, a more favorable one Cast steel material can be used. Furthermore, the component can be designed to suit stress.

Vorteilhafter Weise umfasst das Gussteil weiterhin die Strahldüsen, welche den Hauptbrenner bilden. Diese können beim Gießen der Grundplatte direkt mitgegossen werden.Advantageously, the casting further comprises the jet nozzles, which form the main burner. These can be poured directly when casting the base plate.

In einer alternativen Ausführungsform ist die Grundplatte eine Blechkonstruktion. Auch mit dieser Lösung lassen sich die Herstellungskosten alleine schon wegen deutlich geringerer Rohmaterialkosten im Vergleich zur Variante mit massivem Schmiedmaterial senken.In an alternative embodiment, the base plate is a sheet metal construction. Even with this solution, the manufacturing costs can be reduced alone because of significantly lower raw material costs compared to the version with solid blacksmith material.

Insbesondere bei einer Blechkonstruktion, aber nicht ausschließlich dort, ist des vorteilhaft, wenn sich eine über die Kaltgasseite der Grundplatte hinaus erstreckende umlaufende Wand mit zunehmendem Abstand von der Grundplatte einer Mittelachse des Strahlbrenners annähert. Diese Wand und der sie umgebende, typischerweise zylindrische äußere Gehäuseteil bilden dann eine Art Diffusor, wodurch sich die vom Kompressor bereitgestellte Luftströmung verlangsamt und den Druck vorteilhaft erhöht.In particular, in a sheet metal construction, but not exclusively there, which is advantageous if approaching beyond the cold gas side of the base plate extending circumferential wall with increasing distance from the base plate of a central axis of the jet burner approximates. This wall and the surrounding, typically cylindrical outer housing part then form a kind of diffuser, whereby the air flow provided by the compressor slows down and advantageously increases the pressure.

Beim erfindungsgemäßen Strahlbrenner werden die Luftversorgung des Pilotbrenners und des Hauptbrenners getrennt. Dadurch kann der Pilotbrenner-Luftmassenstrom für die Kühlung des Brenners verwendet werden. Durch die Herstellung des erfindungsgemäßen Strahlbrenners mittels Guss oder die Verwendung einer Blechkonstruktion können nicht nur Kosten gespart, sondern auch zusätzliche Designmerkmale in den Düsenträger integriert werden, die den Betrieb des Verbrennungssystems positiv beeinflussen (z.B. verbesserte Lebensdauer, höhere Rückschlagsicherheit und geringerer Druckverlust). Diese positiven Eigenschaften werden in der vorliegenden Erfindung durch das Einbringen von Kühl- und Spülluftkanälen erreicht.In the jet burner according to the invention, the air supply of the pilot burner and the main burner are separated. This allows the pilot burner air mass flow to be used for cooling the burner. Producing the cast jet burner of the present invention or using a sheet metal construction not only saves costs but also integrates additional design features into the nozzle carriers that positively affect the operation of the combustion system (e.g., improved life, greater recoil safety, and less pressure loss). These positive properties are achieved in the present invention by the introduction of cooling and Spülluftkanälen.

Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen schematisch und nicht maßstäblich:

  • Figur 1 einen Strahlbrenner nach dem Stand der Technik,
  • Figur 2 einen Schnitt durch einen Strahlbrenner senkrecht zu einer Mittelachse des Brenners,
  • Figur 3 einen Schnitt durch einen weiteren Strahlbrenner senkrecht zu einer Mittelachse des Brenners,
  • Figur 4 einen Schnitt durch einen Teil eines Strahlbrenners nach der Erfindung mit Möglichkeiten der Kühlluftentnahme,
  • Figur 5 eine weitere Möglichkeit der Kühlluftentnahme,
  • Figur 6 eine Ausführung des erfindungsgemäßen Kühlkonzepts, bei dem Luft durch einen Kühlkanal in Form eines Hohlraums strömt und
  • Figur 7 einen Schnitt durch einen erfindungsgemäßen Strahlbrenner senkrecht zur Mittelachse mit Blick in den Hohlraum.
The invention will be explained in more detail by way of example with reference to the drawings. Shown schematically and not to scale:
  • FIG. 1 a jet burner according to the prior art,
  • FIG. 2 a section through a jet burner perpendicular to a central axis of the burner,
  • FIG. 3 a section through another jet burner perpendicular to a central axis of the burner,
  • FIG. 4 a section through a portion of a jet burner according to the invention with possibilities of cooling air extraction,
  • FIG. 5 another way of cooling air extraction,
  • FIG. 6 an embodiment of the cooling concept according to the invention, in which air flows through a cooling channel in the form of a cavity, and
  • FIG. 7 a section through a jet burner according to the invention perpendicular to the central axis with a view into the cavity.

Figur 1 zeigt schematisch einen Schnitt durch einen Teil eines Strahlbrenners 1 in Längsrichtung, also entlang der Mittelachse 2 des Brenners 1 nach dem Stand der Technik. Der Brenner 1 weist mindestens eine in einem Düsenträger 3 angeordnete Strahldüse 4 auf. Die Strahldüse 4 umfasst einen Strahldüseneintritt 5 und einen Strahldüsenaustritt 6. An den Strahldüsenaustritt 6 schließt sich die Brennkammer 7 an. Zudem ist die Strahldüse 4 so im Düsenträger 3 angeordnet, dass der Strahldüseneintritt 5 der Rückwand 8 des Brenners 1 zugewandt ist. Die der Brennkammer 7 zugewandte Seite des Strahlbrenners 1 wird als Heißgasseite 9 bezeichnet, die der Brennkammer 7 abgewandte Seite wird als Kaltgasseite 10 bezeichnet. Im Bereich des Strahldüseneintritts 5 der Strahldüse 4 ist eine Brennstoffdüse 11 angeordnet. Durch die Brennstoffdüse 11 wird Brennstoff in die Strahldüse 4 eingedüst. Der Brenner 1 umfasst weiterhin einen radial in Bezug auf die Mittelachse 2 des Brenners 1 äußeren Gehäuseteil 12, der mit dem Düsenträger 3 einen Ringkanal 13 bildet. Durch diesen Ringkanal 13 strömt Luft 14 aus dem Kompressor in Richtung der Rückwand 8 des Brenners 1 und wird dort umgelenkt, so dass sie durch die Strahldüseneintritte 5 in die Strahldüsen 4 gelangt. FIG. 1 schematically shows a section through a portion of a jet burner 1 in the longitudinal direction, ie along the central axis 2 of the burner 1 according to the prior art. The burner 1 has at least one jet nozzle 4 arranged in a nozzle carrier 3. The jet nozzle 4 comprises a jet nozzle inlet 5 and a jet nozzle outlet 6. The jet nozzle outlet 6 is adjoined by the combustion chamber 7. In addition, the jet nozzle 4 is arranged in the nozzle carrier 3, that the jet nozzle inlet 5 of the rear wall 8 of the burner 1 faces. The combustion chamber 7 facing side of the jet burner 1 is referred to as hot gas side 9, the combustion chamber 7 side facing away from the cold gas side 10 is referred to. In the region of the jet nozzle inlet 5 of the jet nozzle 4, a fuel nozzle 11 is arranged. Through the fuel nozzle 11, fuel is injected into the jet nozzle 4. The burner 1 further comprises a radially with respect to the central axis 2 of the burner 1 outer housing part 12 which forms an annular channel 13 with the nozzle carrier 3. Through this annular channel 13, air 14 flows from the compressor in the direction of the rear wall 8 of the burner 1 and is deflected there, so that it passes through the jet nozzle inlet 5 in the jet nozzles 4.

Was Figur 1 nicht zeigt, ist, dass Brenner, insbesondere Vormischbrenner wie der gezeigte Strahlbrenner 1, mit einem zusätzlichen Pilotbrenner ausgestattet sein können, um die stabile Verbrennung über einen weiten Betriebsbereich, insbesondere im Leerlauf und Teillastbereich sicherzustellen. Ein solcher Pilotbrenner ist dann typischerweise auf der Mittelachse 2 des Brenners angeordnet.What FIG. 1 does not show that burners, in particular premix burners such as the jet burner 1 shown, can be equipped with an additional pilot burner to ensure stable combustion over a wide operating range, in particular at idle and part load range. Such a pilot burner is then typically arranged on the central axis 2 of the burner.

Die Figur 2 zeigt schematisch einen Schnitt durch einen Strahlbrenner 1 senkrecht zu einer Mittelachse 2 des Brenners 1. Der Düsenträger 3 weist einen kreisförmigen Querschnitt auf. Innerhalb des Düsenträgers 3 ist eine bestimmte Anzahl an Strahldüsen 4 im Wesentlichen ringförmig angeordnet. Jede Strahldüse 4 weist dabei einen kreisförmigen Querschnitt auf.The FIG. 2 schematically shows a section through a jet burner 1 perpendicular to a central axis 2 of the burner 1. The nozzle carrier 3 has a circular cross-section. Within the nozzle carrier 3, a certain number of jet nozzles 4 is arranged substantially annular. Each jet nozzle 4 has a circular cross section.

Die Figur 3 zeigt schematisch einen Schnitt durch einen Strahlbrenner 101, wobei der Schnitt senkrecht zur Mittelachse des Brenners 101 verläuft. Der Brenner 101 weist ebenfalls einen Düsenträger 3 auf, welcher einen kreisförmigen Querschnitt besitzt und in welchem eine Anzahl innerer und äußerer Strahldüsen 4, 104 angeordnet ist. Die Strahldüsen 4, 104 weisen jeweils einen kreisförmigen Querschnitt auf, wobei die äußeren Strahldüsen 4 eine gleich große oder größere Querschnittsfläche besitzen als die inneren Strahldüsen 104. Die äußeren Strahldüsen 4 sind im Wesentlichen ringförmig innerhalb des Düsenträgers 3 angeordnet und bilden einen äußeren Ring. Die inneren Strahldüsen 104 sind ebenfalls innerhalb des Gehäuses 3 ringförmig angeordnet. Die inneren Strahldüsen 104 bilden einen inneren Ring, der konzentrisch zu dem äußeren Strahldüsenring angeordnet ist.The FIG. 3 schematically shows a section through a jet burner 101, wherein the section is perpendicular to the central axis of the burner 101. The burner 101 also has a nozzle carrier 3, which has a circular cross-section and in which a number of inner and outer jet nozzles 4, 104 is arranged. The jet nozzles 4, 104 each have a circular cross-section, wherein the outer jet nozzles 4 have an equal or larger cross-sectional area than the inner jet nozzles 104. The outer jet nozzles 4 are arranged substantially annularly within the nozzle carrier 3 and form an outer ring. The inner jet nozzles 104 are also arranged annularly within the housing 3. The inner jet nozzles 104 form an inner ring which is concentric with the outer jet nozzle ring.

Die Figuren 2 und 3 zeigen lediglich Beispiele für die Anordnung von Strahldüsen 4, 104 innerhalb eines Strahlbrenners 1, 101. Selbstverständlich sind alternative Anordnungen, ebenso wie die Verwendung einer anderen Anzahl an Strahldüsen 4, 104 möglich. Außerdem kann der Brenner 1, 101 einen Pilotbrenner umfassen.The Figures 2 and 3 merely show examples of the arrangement of jet nozzles 4, 104 within a jet burner 1, 101. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 4, 104 are possible. In addition, the burner 1, 101 may include a pilot burner.

Figur 4 zeigt einen Schnitt durch einen Teil eines Strahlbrenners 15 nach der Erfindung, bei dem die Strahldüsen 16 auf einer Grundplatte 17 angeordnet sind, wobei die Grundplatte 17 Kühlkanäle 18 aufweist, welche beispielsweise bei Verwendung eines Gussprozesses direkt in die Grundplatte 17 mit eingegossen werden können. Dabei können auch die Strahldüsen 16, die den Hauptbrenner (Vormischbrenner) bilden, direkt mitgegossen werden. Die Grundplatte 17 wird über die Kühlluftkanäle 18 gekühlt. FIG. 4 shows a section through a portion of a jet burner 15 according to the invention, in which the jet nozzles 16 are arranged on a base plate 17, wherein the base plate 17 has cooling channels 18, which can be poured, for example, when using a casting process directly into the base plate 17 with. In this case, the jet nozzles 16, which form the main burner (premix burner), can be cast directly. The base plate 17 is cooled by the cooling air channels 18.

Heißgasseitig kann die Grundplatte 17 durch eine Wärmedämmschicht 19 (thermal barrier coating) ergänzt werden. Durch die Kombination von Wärmedämmschichten 19 und effektiver Kühlung ist es unter Umständen möglich, auf beispielsweise Nickelbasislegierungen zu verzichten. Allerdings ist auch bei Verwendung einer Nickelbasislegierung eine Kostenreduzierung zu erwarten, da deutlich weniger Material für ein Gussbauteil notwendig ist.Hot gas side, the base plate 17 can be supplemented by a thermal barrier coating 19 (thermal barrier coating). The combination of thermal barrier coatings 19 and effective cooling, it may be possible to dispense with, for example, nickel-based alloys. However, a cost reduction is to be expected even when using a nickel-based alloy, since significantly less material is required for a cast component.

Wie in Figur 4 weiter dargestellt, kann die Kühlluft 20 entweder aus dem Ringkanal 13 oder aus dem Plenum 21 vor der Grundplatte 17 entnommen werden. Bei Entnahme aus dem Ringkanal 13 wird die Kühlluft 20 durch Öffnungen 22 an einem umlaufenden Rand 23 der Grundplatte 17 dem Kühlkanal 18 zugeführt. Bei Entnahme aus dem Plenum 21 wird die Kühlluft 20 durch Öffnungen 24 auf der Kaltgasseite 10 der Grundplatte 17 dem Kühlkanal 18 zugeführt. Nach erfolgter Kühlung der Grundplatte 17 gelangt die Kühlluft 20 nicht direkt in die Brennkammer 7, sondern wird dem Pilotbrenner (vgl. Figur 6) zugeführt.As in FIG. 4 shown further, the cooling air 20 can be removed either from the annular channel 13 or from the plenum 21 in front of the base plate 17. When removed from the annular channel 13, the cooling air 20 is supplied through openings 22 at a peripheral edge 23 of the base plate 17 to the cooling channel 18. When removed from the plenum 21, the cooling air 20 is supplied through openings 24 on the cold gas side 10 of the base plate 17 to the cooling channel 18. After cooling of the base plate 17, the cooling air 20 does not enter directly into the combustion chamber 7, but is the pilot burner (see. FIG. 6 ).

Durch die hohen Strömungsgeschwindigkeiten in den Strahldüsen 16 (deutlicher Abfall des statischen Drucks) steht hier ein hohes Druckgefälle zur Verfügung, welches genutzt werden kann, um die Kühlkanäle 18 mit Elementen 26 für eine erhöhte Wärmeübertragung (z.B. Rippen oder Vertiefungen 36) und/oder eine Strömungsführung (z.B. Umlenkbleche 35) auszustatten (vgl. Figur 7).Due to the high flow velocities in the jet nozzles 16 (marked drop in the static pressure), a high pressure gradient is available here, which can be used to connect the cooling channels 18 with elements 26 for increased heat transfer (eg ribs or depressions 36) and / or Provide flow guide (eg baffles 35) (see. FIG. 7 ).

Bezieht der Pilot die für seinen Betrieb benötigte Luftmenge im Wesentlichen über die Kühlluftkanäle 18, steht vergleichsweise viel Luft zur Verfügung (ca. 5-12% der gesamten verfügbaren Luftmenge 14), d.h. die Kühlkanäle 18 müssen hier entsprechend groß ausfallen, damit der angestrebte Pilot-Luft-Split, d.h. der Anteil der dem Piloten zugeführten Luft bezogen auf die Gesamtluftmenge 14, bei dem vorgegebenen Differenzdruck auch erreicht wird. In diesem Fall würden die Kühlkanäle 18 ohne oder nur mit wenigen Rippen oder ähnlichen Elementen 26 ausgestattet. Die notwendige Kühlwirkung wird über den erhöhten Massenstrom realisiert.If the pilot relates the amount of air required for his operation substantially via the cooling air ducts 18, comparatively much air is available (about 5-12% of the total available air volume 14), i. the cooling channels 18 must here be correspondingly large, so that the desired pilot air split, i. the proportion of air supplied to the pilot based on the total amount of air 14, is also achieved at the predetermined differential pressure. In this case, the cooling channels 18 would be equipped with no or only a few ribs or similar elements 26. The necessary cooling effect is realized via the increased mass flow.

Figur 5 zeigt eine weitere Möglichkeit der Kühlluftentnahme. Im dargestellten Fall wird die Kühlluft für die Grundplatte 17 (oder zumindest ein Teil der Kühlluft) aus der Grenzschicht an der Umlenkung 30 vom Ringkanal 13 in das Plenum 21 entnommen. Durch diese Entnahme wird die Grenzschicht stabilisiert und liegt länger an. Hierdurch ergibt sich ein geringerer Umlenkdruckverlust. Der gewonnene Druck kann z.B. für eine höhere Strahlgeschwindigkeit verwendet werden. Über eine in der die Strahldüsen 16 umgebenden, an die Grundplatte 17 anschließenden Wandung 31 des Düsenträgers angeordnete, zur Kaltgasseite 10 des Strahlbrenners 15 hin geöffnete und in die Grundplatte 17 mündende Kühlluftleitung 32 gelangt die Kühlluft 20 in den Kühlkanal 18 der Grundplatte 17. FIG. 5 shows another way of cooling air extraction. In the illustrated case, the cooling air for the base plate 17 (or at least a portion of the cooling air) is removed from the boundary layer at the deflection 30 from the annular channel 13 into the plenum 21. This removal stabilizes the boundary layer and lasts longer. This results in a lower Umlenkdruckverlust. The obtained pressure can be used eg for a higher jet speed. About a in the jet nozzles 16 surrounding, adjoining the base plate 17 wall 31 of the nozzle carrier, open to the cold gas side 10 of the jet burner 15 and opening into the base plate 17 cooling air line 32, the cooling air 20 enters the cooling channel 18 of the base plate 17th

Figur 6 zeigt eine bevorzugte Ausführung des erfindungsgemäßen Kühlkonzepts, bei dem Luft durch einen Kühlkanal 18 strömt, wobei sich der Kühlkanal 18 in der Art eines Hohlraums nahezu über die gesamte Fläche der Grundplatte 17 erstreckt und wobei die Kühlluft 20, nachdem sie den Kühlkanal 18 durchströmt hat, dem Pilotbrenner 33 als Pilotluft 27 zugeführt wird. Die Luftversorgung des Pilotbrenners 33 erfolgt hierbei direkt und ausschließlich über den Kühlkanal 18. FIG. 6 shows a preferred embodiment of the cooling concept according to the invention, in which air flows through a cooling channel 18, wherein the cooling channel 18 extends in the manner of a cavity almost over the entire surface of the base plate 17 and wherein the cooling air 20, after having passed through the cooling channel 18, the pilot burner 33 is supplied as pilot air 27. The air supply of the pilot burner 33 takes place here directly and exclusively via the cooling channel 18.

Die über die Kaltgasseite 10 der Grundplatte 17 hinaus sich erstreckende umlaufende Wand 34 nähert sich mit zunehmendem Abstand von der Grundplatte 17 einer Mittelachse 2 des Strahlbrenners 15 an. Diese Wand 34, und der sie umgebende, typischerweise zylindrische äußere Gehäuseteil 12 bilden dann eine Art Diffusor, wodurch sich die vom Kompressor bereitgestellte Luftströmung 14 verlangsamt und der Druck sich vorteilhaft erhöht.The over the cold gas side 10 of the base plate 17 also extending circumferential wall 34 approaches with increasing distance from the base plate 17 of a central axis 2 of the Jet burner 15 on. This wall 34, and the surrounding, typically cylindrical outer housing part 12 then form a kind of diffuser, whereby the air flow 14 provided by the compressor slows down and the pressure increases advantageously.

Figur 7 zeigt einen Schnitt durch einen erfindungsgemäßen Strahlbrenner 15 senkrecht zur Mittelachse 2, der sich vorteilhafter Weise mittels einer Blechkonstruktion verwirklichen lässt, da sich der Kühlkanal 18 im Wesentlichen über die Grundfläche der Grundplatte 17 erstreckt, ggf. nur unterbrochen durch stützende Elemente. Im vorliegenden Beispiel der Figur 7 wird die Kühlluft 20 zwischen Heißgas- 9 und Kaltgasseite 10 der Grundplatte 17 von radial außen nach radial innen geführt (der Pilotbrenner ist nicht gezeigt). Dabei muss die nach innen zum Piloten strömende Kühlluft 20 die Strahldüsen 4 der Vormischpassagen des Hauptbrenners 25 umströmen. FIG. 7 shows a section through a jet burner 15 according to the invention perpendicular to the central axis 2, which can be realized advantageously by means of a sheet metal construction, since the cooling channel 18 extends substantially over the base of the base plate 17, possibly only interrupted by supporting elements. In the present example the FIG. 7 the cooling air 20 between hot gas 9 and cold gas side 10 of the base plate 17 is guided from radially outside to radially inside (the pilot burner is not shown). In this case, the cooling air 20 flowing inwards towards the pilot must flow around the jet nozzles 4 of the premix passages of the main burner 25.

Um Totwassergebiete hinter den Strahldüsen 4 zu vermeiden oder zumindest zu minimieren, können Elemente 26 für erhöhte Wärmeübertragung bzw. Strömungsführung in den Strömungspfad eingebracht sein, wie Figur 7 mit den Umlenkblechen 35 (spoilers) oder Vertiefungen 36 (dimples) zeigt.In order to avoid or at least minimize dead water areas behind the jet nozzles 4, elements 26 for increased heat transfer or flow guidance can be introduced into the flow path, such as FIG. 7 with the baffles 35 (spoilers) or depressions 36 (dimples) shows.

Claims (12)

  1. Jet burner (15) having a hot gas side (9) which, in operation, is oriented toward a combustion chamber (7) and a cold gas side (10) which is oriented away from the combustion chamber (7), comprising a base plate (17) on which there are arranged multiple jet nozzles (16), wherein the base plate (17) has at least one cooling duct (18) which opens into a burner stage which comprises a pilot burner (33) arranged on the base plate (17), characterized in that the cooling duct (18) extends over the area of the base plate (17) such that cooling air (20) is guided from radially outside to radially inside between the hot gas side (9) and cold gas side (10) of the base plate (17), wherein the cooling air (20) flows around the jet nozzles (16) and is guided exclusively to the pilot burner (33).
  2. Jet burner (15) according to Claim 1, wherein the air required for operation of the pilot burner (33) can be supplied from the cooling duct (18).
  3. Jet burner (15) according to either of Claims 1 and 2, wherein the base plate (17) has on its hot gas side a thermal barrier coating (19).
  4. Jet burner (15) according to one of the preceding claims, wherein the at least one cooling duct (18) can be charged with cooling air (20) via an opening (22) on a circumferential rim (23) of the base plate (17).
  5. Jet burner (15) according to one of Claims 1 to 3, wherein the at least one cooling duct (18) can be charged with cooling air (20) via an opening (24) on the cold gas side (10) of the base plate (17).
  6. Jet burner (15) according to one of Claims 1 to 3, wherein the at least one cooling duct (18) can be charged via a cooling air line (32) which is arranged in a wall (31) surrounding the jet nozzles (16) and adjoining the base plate (17), and which is open toward the cold gas side (10) of the jet burner (15) and opens into the base plate (17).
  7. Jet burner (15) according to one of the preceding claims, wherein the cooling duct (18) in the base plate (17) has elements (26) for increased heat transfer and flow guiding.
  8. Jet burner (15) according to Claim 7, wherein the elements(26) are embodied as spoilers (35) or dimples (36).
  9. Jet burner (15) according to one of the preceding claims, wherein at least the base plate (17) is a cast part.
  10. Jet burner (15) according to Claim 9, wherein the cast part comprises jet nozzles (16).
  11. Jet burner (15) according to one of Claims 1 to 8, wherein at least the base plate (17) is a sheet metal construction.
  12. Jet burner (15) according to one of the preceding claims, wherein a circumferential wall (34) extending beyond the cold gas side (10) of the base plate (17) approaches a central axis (2) of the jet burner (15) with increasing distance from the base plate (17).
EP14705083.5A 2013-03-13 2014-02-07 Jet burner with cooling duct in the base plate Active EP2954262B1 (en)

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DE102013204307.4A DE102013204307A1 (en) 2013-03-13 2013-03-13 Jet burner with cooling channel in the base plate
PCT/EP2014/052410 WO2014139738A1 (en) 2013-03-13 2014-02-07 Jet burner with cooling duct in the base plate

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EP2980482A1 (en) * 2014-07-30 2016-02-03 Siemens Aktiengesellschaft Burner for a combustion engine and combustion engine
US10634353B2 (en) * 2017-01-12 2020-04-28 General Electric Company Fuel nozzle assembly with micro channel cooling
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US20160018109A1 (en) 2016-01-21
WO2014139738A1 (en) 2014-09-18
CN105102893B (en) 2017-06-06
DE102013204307A1 (en) 2014-09-18
US10088163B2 (en) 2018-10-02
CN105102893A (en) 2015-11-25
EP2954262A1 (en) 2015-12-16

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