EP2256413A1 - Burner, operating method and fitting method - Google Patents
Burner, operating method and fitting method Download PDFInfo
- Publication number
- EP2256413A1 EP2256413A1 EP09161187A EP09161187A EP2256413A1 EP 2256413 A1 EP2256413 A1 EP 2256413A1 EP 09161187 A EP09161187 A EP 09161187A EP 09161187 A EP09161187 A EP 09161187A EP 2256413 A1 EP2256413 A1 EP 2256413A1
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- EP
- European Patent Office
- Prior art keywords
- pilot
- insert
- cone
- pilot cone
- burner
- 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.)
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Classifications
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- 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
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- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- 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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
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- 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
- F23R2900/00017—Assembling combustion chamber liners or subparts
Definitions
- the present invention relates to a burner comprising a pilot cone and a carrier insert. Furthermore, the invention relates to an operating method for increasing the service life of a burner. In addition, the invention relates to a mounting method for mounting and dismounting a pilot cone assembly of a burner from a carrier insert, the pilot cone assembly comprising a pilot cone and an inner pilot insert, wherein the inner pilot insert is disposed between the carrier insert and the pilot cone.
- gas turbines include the following components: a compressor to compress air; a combustion chamber for generating a hot gas by burning fuel in the presence of compressed air generated by the compressor; and a turbine for relaxing the hot gas generated by the combustion chamber. It is also known that gas turbines give off unwanted nitrogen oxides (NOx) and carbon monoxide (CO).
- NOx nitrogen oxides
- CO carbon monoxide
- One factor that is known to affect the emission of NOx is the combustion temperature. The amount of discharged NOx reduces as the combustion temperature is lowered. However, higher combustion temperatures are desirable to achieve higher efficiency and oxidation of the CO.
- Two-stage combustion systems have been developed to ensure efficient combustion and reduced emissions of NOx.
- diffusion combustion is performed in the first stage to achieve the ignition and stability of the flame.
- premixed combustion is performed to reduce emissions of NOx.
- a typical prior art combustor 10 includes a nozzle housing 6 having a nozzle body lower portion 5.
- An ignition nozzle 1 for diffusion of the fuel having an injection port 4 for the pilot fuel passes through the nozzle housing 6 and is fixed to the lower part 5 of the nozzle housing.
- the main fuel nozzles 2 are parallel to the ignition nozzle 1 through the nozzle housing 6 and are fixed to the lower part 5 of the nozzle housing.
- the fuel inlets 16 supply the main fuel nozzles 2 with fuel.
- a main combustion zone 9 is formed within the liner 19.
- a pilot cone 20 protrudes from the vicinity of the injection port 4 for the pilot fuel of the ignition nozzle 1 and has a widened end 22 in addition to the main combustion zone 9.
- the pilot cone 20 has a linear profile 21, which forms a zone 23 for the pilot flame.
- the compressed air 101 flows from the compressor 50 between support ribs 7 through the main fuel swirlers 8 into the main combustion zone 9.
- Each main fuel swirling device 8 has a plurality of swirl vanes 80.
- the compressed air 12 passes through a set of plates 10 located inside the ignition swirler 11 are in the zone of pilot light.
- the compressed air 12 mixes within the pilot cone 20 with the pilot fuel 30 and is transported to the zone 23 of the pilot flame, where it burns.
- Radiation flame based combustion systems offer advantages over spin stabilized systems due to the distributed heat release zones and the lack of swirl induced swirls, especially from a thermoacoustic point of view.
- the jet flames are stabilized by mixing in hot recirculating gases.
- the necessary temperatures of the recirculation zone can in gas turbines, especially in lower part load range, not guaranteed by the known ring arrangement of the beams with a central recirculation zone. Therefore, an additional piloting is also required here, which also consists of a pilot burner and a pilot cone.
- the pilot cone is welded to a carrier insert.
- the combustion chamber is supplied, for example by means of suitable passages, fuel or combustion air.
- thermal expansions occur. These are different thermal expansions of the various components as well as the radial thermal expansion of the pilot cone. Due to the fixed welded joint, however, these thermal strains are hindered, which leads to very high stresses on the cone itself. Due to the stresses occurring during operation, the components are damaged, for example, by cracks and must therefore be replaced sooner. Therefore, the prevention of thermal expansion leads to a reduction in the cyclic life of the components, in particular the cone.
- this object is achieved according to the invention by specifying a burner, comprising a pilot cone and a carrier insert, wherein the pilot cone and the carrier insert are thermally decoupled.
- the invention is based on the recognition that the service life of the components, ie the pilot cone and the carrier insert by the obstruction of the thermal expansion of the components in the radial and axial direction and the associated voltages occurring is significantly impaired. With the help of the invention, this is precisely what is prevented.
- the thermal decoupling of the two components leads to the thermal expansions being made possible, which in turn leads to a longer service life of the pilot cone by reducing the voltages.
- an inner pilot insert is provided between the carrier insert and the pilot cone. This runs essentially parallel to the pilot cone.
- openings are provided on the inner pilot insert. These openings may be, for example, holes. Through these openings cooling air is guided, which causes a baffle cooling at the pilot cone. This impingement cooling enables more effective cooling of the pilot cone. As a result, cooling with a relatively low cooling air flow is possible, whereby cooling air can be saved.
- the openings may have different diameters, depending on the cooling requirement of the pilot cone. Thus, more cooling air can be supplied at critical points than at non-critical points. For the same reason, the openings may also be distributed differently.
- the pilot cone is welded to the inner pilot insert.
- the welding is provided at the upstream end of the pilot insert. It can be seen downstream in the direction of flow of the fuel of the burner, upstream against the flow direction of the burner.
- the inner pilot insert is further bolted to the carrier insert.
- the pilot cone is attached via the inner pilot insert to the carrier insert.
- a defined gap is provided between the pilot cone and the carrier insert.
- the gap now allows thermal expansion in the radial and axial directions. This gap is calculated so that after reaching the operating temperature the gap is closed.
- the cone seals in operation as in the tightly welded cone that is, as in a cone according to the prior art (vg. Fig.2 ). In this case, however, the voltages are lower, resulting in a longer life of the cone and the carrier use.
- a gas turbine is designed with such a burner.
- this object is achieved according to the invention by specifying an operating method for increasing the service life of a burner, which comprises a pilot cone and a carrier insert, wherein the pilot cone is arranged at such a distance that a defined gap is provided between pilot cone and carrier insert, which in the Operation is substantially closed by the thermal expansion.
- the cone is cold, for example, directly on the inner pilot insert. After reaching the operating temperature, the gap is closed by thermally stretching either the cone alone or the cone and the carrier insert. Thus, the cone seals tightly during operation.
- an inner pilot insert with openings is present between the pilot cone and a carrier insert, by means of which the pilot cone is cooled by impingement air.
- the resulting impingement air cooling cools the cone with a small flow of cooling air, which allows cooling air to be saved.
- this object is achieved by specifying a mounting method for mounting and dismounting a pilot cone assembly of a burner from a carrier insert, wherein the pilot cone assembly comprises a pilot cone and an inner pilot insert, wherein the inner pilot insert between carrier insert and pilot cone arranged is, wherein the inner pilot insert is bolted to the carrier insert during assembly / disassembly.
- Fig. 2 shows a schematic representation of a burner with a pilot cone according to the prior art.
- the pilot cone 20 is welded to a carrier insert 110 and serves as a transition between pilot burner 140 and carrier insert 110, which abuts against the combustion chamber inner wall 120. This has, inter alia, passages which lead the combustion air to the combustion chamber 130.
- the pilot cone 20 is externally welded to the carrier insert 110 with at least one welding point 170. Inside it sits by means of a sliding seat 150 on the pilot burner 140. In operation, however, thermal induced strains occur, inter alia, also in the radial direction. Due to the weld and the sliding seat 150, however, this thermally occurring strain is severely limited. As a result, strong, very high voltages occur on the cone 20. However, these thermal stresses lead to a reduction of the cyclic life.
- Fig. 3 shows a burner according to the invention with pilot cone 100 according to the invention and carrier insert 110.
- This instead of the weld 170 between carrier insert 110 and pilot cone 200 now has a defined gap 180.
- the gap 180 allows thermal expansion in the radial 220 as well as in the axial 230 direction.
- the carrier insert 110 and the pilot cone 200 are thus decoupled and may, for example, expand to different extents during operation.
- an inner pilot insert 190 is provided between pilot cone 200 and carrier insert 110.
- This has openings 160 at suitable locations. This can be, for example, small holes. Through these openings 160, cooling air exits in the direction of the pilot cone 200. As a result, the pilot cone 200 is cooled.
- the case made on the pilot cone 200 cooling corresponds to an impingement cooling. This has the significant advantage that only a small flow of cooling air is needed to cool the pilot cone 200.
- the openings 160 may be evenly distributed over the inner pilot insert 190, or accumulated at particularly critical locations. Thus, an efficient cooling of the pilot cone 200 is effected, which also has a life-prolonging effect. In addition, the low cooling air consumption can reduce the NOx levels during combustion.
- the inner pilot insert 190 and the pilot cone 200 are connected to one another at a welding point 280 with each other welded. The welding point 280 is mounted upstream, since there prevail relatively lower temperatures than in the combustion chamber. This promotes the durability of the welding point 280.
- the pilot cone 200 is fastened to the carrier insert 110 via the inner pilot insert 190.
- Fig. 4 shows the burner according to the invention with pilot cone 200 and carrier insert 110 in the cold state
- Fig. 5 the burner according to the invention with pilot cone 200 and carrier insert 110 in operation.
- the pilot cone 200 expands in the axial direction 230 and in the radial direction 220.
- the gap 180 is calculated so that after reaching the operating temperature of the pilot cone 200 on the support insert 110 is almost applied, that is, the gap 180 is almost closed.
- the pilot cone 200 seals in operation like a welded cone. Due to the allowed thermal expansions, however, the voltages are lower; whereby the life of both the pilot cone 200 and the carrier insert 110 increases. Also disturbances of the operation by faulty component components (fine cracks etc) are avoided.
- Fig. 6 shows a mounting of the pilot cone 200 of the burner according to the invention.
- the inner pilot insert 190 is fastened to the carrier insert 110 via a screw connection 250.
- the pilot cone assembly that is, the pilot cone 200 itself as well as the inner pilot insert 190 and the carrier insert 110 can thus be easily assembled and disassembled.
- the carrier insert 110 as well as the pilot cone 200 can be easily replaced separately. This saves on the one hand costs by saving time on the other costs by the separately exchangeable components themselves.
- the pilot cone 200 and the inner pilot insert 190 are thus installed "forward" through the screw 250.
- the inventive method and the burner according to the invention with a thermally decoupled pilot cone 200 and the carrier insert 110 it is thus possible to substantially reduce the stresses on the pilot cone 200.
- the pilot cone 200 and the carrier insert 110 according to the invention have a longer service life.
- By the burner according to the invention with the inner pilot insert 190 also an impingement cooling of the pilot cone 200 is possible. This leads to a significant cooling air savings.
- the defined use of impingement cooling at particularly critical points represents a further increase in the service life of the individual components.
- the improved assembly method increases the assembly / disassembly of the pilot cone assembly.
- the actual decoupling between pilot cone 200 and carrier insert 110 contributes to improved assembly / disassembly of both components.
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
Abstract
Description
Die vorliegende Erfindung betrifft einen Brenner umfassend einem Pilotkonus sowie einen Trägereinsatz. Weiterhin betrifft die Erfindung ein Betriebsverfahren zur Erhöhung der Lebensdauer eines Brenners. Zudem betrifft die Erfindung ein Montageverfahren zum Montieren und Demontieren einer PilotKonus Baugruppe eines Brenners von einem Trägereinsatz, wobei die Pilot-Konus Baugruppe einen Pilotkonus sowie einen inneren Piloteinsatz umfasst, wobei der innere Piloteinsatz zwischen Trägereinsatz und Pilotkonus angeordnet ist.The present invention relates to a burner comprising a pilot cone and a carrier insert. Furthermore, the invention relates to an operating method for increasing the service life of a burner. In addition, the invention relates to a mounting method for mounting and dismounting a pilot cone assembly of a burner from a carrier insert, the pilot cone assembly comprising a pilot cone and an inner pilot insert, wherein the inner pilot insert is disposed between the carrier insert and the pilot cone.
Es ist bekannt, dass Gasturbinen folgende Komponenten enthalten: einen Verdichter, um Luft zu verdichten; eine Brennkammer zur Erzeugung eines heißen Gases, indem Brennstoff in der Anwesenheit von verdichteter Luft, die von dem Verdichter erzeugt wurde, verbrannt wird; und eine Turbine für die Entspannung des heißen Gases, das von der Brennkammer erzeugt wurde. Weiterhin ist bekannt, dass Gasturbinen unerwünschte Stickstoffoxide (NOx) und Kohlenmonoxid (CO) abgeben. Ein Faktor, der bekanntermaßen die Emission von NOx beeinflusst, ist die Verbrennungstemperatur. Der Umfang des abgegebenen NOx reduziert sich, wenn die Verbrennungstemperatur gesenkt wird. Allerdings sind höhere Verbrennungstemperaturen wünschenswert, um einen höheren Wirkungsgrad und eine Oxidation des CO zu erreichen.It is known that gas turbines include the following components: a compressor to compress air; a combustion chamber for generating a hot gas by burning fuel in the presence of compressed air generated by the compressor; and a turbine for relaxing the hot gas generated by the combustion chamber. It is also known that gas turbines give off unwanted nitrogen oxides (NOx) and carbon monoxide (CO). One factor that is known to affect the emission of NOx is the combustion temperature. The amount of discharged NOx reduces as the combustion temperature is lowered. However, higher combustion temperatures are desirable to achieve higher efficiency and oxidation of the CO.
Man hat zweistufige Verbrennungssysteme entwickelt, die für eine effiziente Verbrennung und reduzierte Emissionen von NOx sorgen. In einem zweistufigen Verbrennungssystem wird in der ersten Stufe eine Diffusionsverbrennung durchgeführt, um die Zündung und die Stabilität der Flamme zu erreichen. In der zweiten Stufe wird eine Verbrennung mit Vormischung durchgeführt, um die Emissionen von NOx zu verringern.Two-stage combustion systems have been developed to ensure efficient combustion and reduced emissions of NOx. In a two-stage combustion system, diffusion combustion is performed in the first stage to achieve the ignition and stability of the flame. In the second stage, premixed combustion is performed to reduce emissions of NOx.
Wie in
Die verdichtete Luft 101 strömt von dem Verdichter 50 zwischen Stützrippen 7 durch die Hauptbrennstoffverwirbelungsvorrichtungen 8 in die Hauptverbrennungszone 9. Jede Hauptbrennstoffverwirbelungsvorrichtung 8 verfügt über eine Vielzahl von Verwirbelungsblechen 80. Die verdichtete Luft 12 dringt durch einen Satz von Blechen 10, die sich innerhalb der Zündverwirbelungsvorrichtung 11 befinden, in die Zone der Zündflamme ein. Die verdichtete Luft 12 vermischt sich innerhalb des Pilotkonus 20 mit dem Zündbrennstoff 30 und wird in die Zone 23 der Zündflamme transportiert, wo sie verbrennt.The
Ein anderes Brennersystem ist das auf Strahlflammen basierte Verbrennungssystem. Auf Strahlflammen basierende Verbrennungssysteme bieten gegenüber drallstabilisierten Systemen aufgrund der verteilten Wärmefreisetzungszonen und der fehlenden drallinduzierten Wirbel, insbesondere aus thermoakustischer Sicht Vorteile.Another burner system is the jet flame based combustion system. Radiation flame based combustion systems offer advantages over spin stabilized systems due to the distributed heat release zones and the lack of swirl induced swirls, especially from a thermoacoustic point of view.
Die Strahlflammen werden durch Einmischen heißer rezirkulierender Gase stabilisiert. Die hierfür nötigen Temperaturen der Rezirkulationszone können in Gasturbinen, insbesondere im unteren Teillastbereich, durch die bekannte Ringanordnung der Strahlen mit einer zentralen Rezirkulationszone nicht gewährleistet werden. Daher ist auch hier eine zusätzliche Pilotierung benötigt, welche ebenfalls aus einem Pilotbrenner und einem Pilotkonus besteht.The jet flames are stabilized by mixing in hot recirculating gases. The necessary temperatures of the recirculation zone can in gas turbines, especially in lower part load range, not guaranteed by the known ring arrangement of the beams with a central recirculation zone. Therefore, an additional piloting is also required here, which also consists of a pilot burner and a pilot cone.
Der Pilotkonus ist dabei an einen Trägereinsatz angeschweißt. Durch diesen Trägereinsatz wird beispielsweise mittels geeigneter Passagen, Brennstoff oder Verbrennungsluft der Brennkammer zugeführt. Im Betrieb treten thermische Expansionen auf. Es handelt sich hierbei um unterschiedliche thermische Expansionen der verschiedenen Bauteile als auch durch die radiale thermische Expansion des Pilotkonus. Durch die feste Schweißverbindung werden diese thermischen Dehnungen jedoch behindert, was zu sehr hohen Spannungen am Konus selber führt. Durch die im Betrieb auftretenden Spannungen werden die Bauteile beispielsweise durch Risse beschädigt und müssen somit eher ausgetauscht werden. Daher führen die Verhinderung der thermischen Expansion zu einer Verringerung der zyklischen Lebensdauer der Bauteile, insbesondere des Konus.The pilot cone is welded to a carrier insert. Through this carrier insert the combustion chamber is supplied, for example by means of suitable passages, fuel or combustion air. During operation, thermal expansions occur. These are different thermal expansions of the various components as well as the radial thermal expansion of the pilot cone. Due to the fixed welded joint, however, these thermal strains are hindered, which leads to very high stresses on the cone itself. Due to the stresses occurring during operation, the components are damaged, for example, by cracks and must therefore be replaced sooner. Therefore, the prevention of thermal expansion leads to a reduction in the cyclic life of the components, in particular the cone.
Es ist daher eine Aufgabe der vorliegenden Erfindung, einen Brenner anzugeben welcher eine längere Lebensdauer aufweist. Weiterhin ist es eine Aufgabe ein Verfahren zur Erhöhung der Lebensdauer eines Brenners anzugeben. Zudem ist es eine weitere Aufgabe der Erfindung ein Montageverfahren für einen Brenner anzugeben.It is therefore an object of the present invention to provide a burner which has a longer life. Furthermore, it is an object to provide a method for increasing the life of a burner. In addition, it is a further object of the invention to provide an assembly method for a burner.
Bezogen auf den Brenner wird diese Aufgabe erfindungsgemäß durch die Angabe eines Brenners gelöst, umfassend einem Pilotkonus sowie einen Trägereinsatz, wobei der Pilotkonus und der Trägereinsatz thermisch entkoppelt sind.Relative to the burner, this object is achieved according to the invention by specifying a burner, comprising a pilot cone and a carrier insert, wherein the pilot cone and the carrier insert are thermally decoupled.
Die Erfindung geht von der Erkenntnis aus, dass die Lebensdauer der Bauteile, d.h. des Pilotkonus und des Trägereinsatzes durch die Behinderung der thermische Expansion der Bauteile in radialer und axialer Richtung und die damit verbundenen auftretenden Spannungen wesentlich beeinträchtigt ist. Mithilfe der Erfindung wird nun genau das verhindert. Die thermische Entkopplung der beiden Bauteile führt dazu, dass die thermischen Expansionen ermöglicht werden, was wiederum zu einer höheren Lebensdauer des Pilotkonus durch eine Verringerung der Spannungen führt.The invention is based on the recognition that the service life of the components, ie the pilot cone and the carrier insert by the obstruction of the thermal expansion of the components in the radial and axial direction and the associated voltages occurring is significantly impaired. With the help of the invention, this is precisely what is prevented. The thermal decoupling of the two components leads to the thermal expansions being made possible, which in turn leads to a longer service life of the pilot cone by reducing the voltages.
Bevorzugt ist zwischen Trägereinsatz und Pilotkonus ein innerer Piloteinsatz vorgesehen. Dieser verläuft im Wesentlichen parallel zum Pilotkonus.Preferably, an inner pilot insert is provided between the carrier insert and the pilot cone. This runs essentially parallel to the pilot cone.
In bevorzugter Ausgestaltung sind am inneren Piloteinsatz Öffnungen vorgesehen. Diese Öffnungen können beispielsweise Bohrungen sein. Durch diese Öffnungen wird Kühlluft geführt, welche eine Prallkühlung am Pilotkonus bewirkt. Durch diese Prallkühlung ist eine effektivere Kühlung des Pilotkonus möglich. Dadurch ist eine Kühlung mit einem relativ geringen Kühlluftstrom möglich, wodurch sich Kühlluft einsparen lässt. Die Öffnungen können dabei unterschiedliche Durchmesser aufweisen, je nach Kühlungsbedarf des Pilotkonus. So kann an kritischen Stellen mehr Kühlluft zugeführt werden als an nicht kritischen Stellen. Aus demselben Grund können die Öffnungen auch unterschiedlich verteilt sein.In a preferred embodiment, openings are provided on the inner pilot insert. These openings may be, for example, holes. Through these openings cooling air is guided, which causes a baffle cooling at the pilot cone. This impingement cooling enables more effective cooling of the pilot cone. As a result, cooling with a relatively low cooling air flow is possible, whereby cooling air can be saved. The openings may have different diameters, depending on the cooling requirement of the pilot cone. Thus, more cooling air can be supplied at critical points than at non-critical points. For the same reason, the openings may also be distributed differently.
Bevorzugt ist der Pilotkonus mit dem inneren Piloteinsatz verschweißt. Die Verschweißung ist dabei am stromaufwärtigem Ende des Piloteinsatzes vorgesehen. Dabei ist stromabwärts in Strömungsrichtung des Brennstoffes des Brenners zu sehen, stromaufwärts entgegen der Strömungsrichtung des Brenners. In bevorzugter Ausgestaltung ist der innere Piloteinsatz weiter mit dem Trägereinsatz verschraubt. Somit wird der Pilotkonus über den inneren Piloteinsatz mit dem Trägereinsatz befestigt. Durch diese Schraubverbindung ist ein einfaches Lösen des Pilotkonus und des inneren Piloteinsatzes möglich.Preferably, the pilot cone is welded to the inner pilot insert. The welding is provided at the upstream end of the pilot insert. It can be seen downstream in the direction of flow of the fuel of the burner, upstream against the flow direction of the burner. In a preferred embodiment, the inner pilot insert is further bolted to the carrier insert. Thus, the pilot cone is attached via the inner pilot insert to the carrier insert. By this screw connection a simple release of the pilot cone and the inner pilot insert is possible.
Bevorzugt ist zwischen Pilotkonus und Trägereinsatz ein definierter Spalt vorgesehen. Der Spalt erlaubt nun ein thermisches Dehnen in radialer und axialer Richtung. Dieser Spalt ist derart berechnet, dass nach Erreichen der Betriebstemperatur der Spalt geschlossen ist. Dadurch dichtet der Konus im Betrieb wie beim fest angeschweißten Konus, das heißt wie bei einem Konus nach dem Stand der Technik (vlg.
Bevorzugt ist eine Gasturbine mit einem solchen Brenner ausgestaltet.Preferably, a gas turbine is designed with such a burner.
Bezogen auf das Verfahren wird diese Aufgabe erfindungsgemäß durch die Angabe eines Betriebsverfahren zur Erhöhung der Lebensdauer eines Brenners gelöst, welches einen Pilotkonus und einen Trägereinsatz umfasst, wobei der Pilotkonus derart beabstandet angeordnet ist, dass ein definierter Spalt zwischen Pilotkonus und Trägereinsatz vorgesehen ist, welcher im Betrieb durch die thermische Expansion in wesentlichen geschlossen wird. Der Konus liegt im kalten Zustand beispielsweise direkt am inneren Piloteinsatz an. Nach Erreichen der Betriebstemperatur wird durch thermisches Dehnen entweder des Konus alleine oder des Konus und des Trägereinsatzes der Spalt geschlossen. Somit dichtet der Konus im Betrieb fest ab.In relation to the method, this object is achieved according to the invention by specifying an operating method for increasing the service life of a burner, which comprises a pilot cone and a carrier insert, wherein the pilot cone is arranged at such a distance that a defined gap is provided between pilot cone and carrier insert, which in the Operation is substantially closed by the thermal expansion. The cone is cold, for example, directly on the inner pilot insert. After reaching the operating temperature, the gap is closed by thermally stretching either the cone alone or the cone and the carrier insert. Thus, the cone seals tightly during operation.
Bevorzugt ist zwischen Pilotkonus und einen Trägereinsatz ein innerer Piloteinsatz mit Öffnungen vorhanden, mittels welchem der Pilotkonus prallluftgekühlt wird. Die so entstandene Prallluftkühlung kühlt den Konus mit geringem Kühlluftstrom, wodurch sich Kühlluft einsparen lässt.Preferably, an inner pilot insert with openings is present between the pilot cone and a carrier insert, by means of which the pilot cone is cooled by impingement air. The resulting impingement air cooling cools the cone with a small flow of cooling air, which allows cooling air to be saved.
Bezogen auf das Montageverfahren wird diese Aufgabe erfindungsgemäß durch die Angabe eines Montageverfahren zum Montieren und Demontieren einer Pilot-Konus Baugruppe eines Brenners von einen Trägereinsatz gelöst, wobei die PilotKonus Baugruppe einen Pilotkonus sowie einen inneren Piloteinsatz umfasst, wobei der innere Piloteinsatz zwischen Trägereinsatz und Pilotkonus angeordnet ist, wobei der innere Piloteinsatz mit dem Trägereinsatz beim montieren/demontieren verschraubt wird. Durch diese Verschraubung lässt sich die Pilot-Konus Baugruppe vereinfacht ausbauen. Die getrennten Baugruppen, das heißt die Pilot-Konus Baugruppe und der Trägereinsatz, führen zu verbesserten Montage/Demontagebedingungen. Zudem können die Bauteile vereinfacht einzeln bei einer Beschädigung ausgetauscht werden.With respect to the assembly method, this object is achieved by specifying a mounting method for mounting and dismounting a pilot cone assembly of a burner from a carrier insert, wherein the pilot cone assembly comprises a pilot cone and an inner pilot insert, wherein the inner pilot insert between carrier insert and pilot cone arranged is, wherein the inner pilot insert is bolted to the carrier insert during assembly / disassembly. By this screwing can be the Simplify pilot cone assembly removal. The separate assemblies, ie the pilot cone assembly and the carrier insert, result in improved assembly / disassembly conditions. In addition, the components can be easily replaced individually in the event of damage.
Im Folgenden wird die Erfindung beispielhaft anhand einer Zeichnung näher erläutert.In the following the invention will be explained by way of example with reference to a drawing.
Darin zeigt in vereinfachter und nicht maßstäblicher Darstellung:
- FIG 1
- eine schematische Darstellung einer Gasturbine nach dem Stand der Technik,
- FIG 2
- eine Darstellung eines Brenner mit einen Pilotkonus nach dem Stand der Technik,
- FIG 3
- einen erfindungsgemäßen Brenner mit Pilotkonus und Trägereinsatz,
- FIG 4
- den erfindungsgemäßen Brenner mit Pilotkonus und Trä- gereinsatz im kalten Zustand,
- FIG 5
- den erfindungsgemäßen Brenner mit Pilotkonus und Trä- gereinsatz im Betrieb,
- FIG 6
- eine Befestigung des Pilotkonus des erfindungsgemäßen Brenners.
- FIG. 1
- a schematic representation of a gas turbine according to the prior art,
- FIG. 2
- a representation of a burner with a pilot cone according to the prior art,
- FIG. 3
- a burner according to the invention with pilot cone and carrier insert,
- FIG. 4
- the burner according to the invention with pilot cone and carrier insert in the cold state,
- FIG. 5
- the burner according to the invention with pilot cone and carrier insert in operation,
- FIG. 6
- an attachment of the pilot cone of the burner according to the invention.
Gleiche Teile sind in allen Figuren mit denselben Bezugszeichen versehen.Identical parts are provided with the same reference numerals in all figures.
Dieses wird mithilfe der Erfindung nun vermieden.
Durch das erfindungsgemäße Verfahren als auch den erfindungsgemäßen Brenner mit einem thermisch entkoppelten Pilotkonus 200 und dem Trägereinsatz 110 ist es somit möglich, die Spannungen am Pilotkonus 200 wesentlich zu verringern. Der Pilotkonus 200 als auch der Trägereinsatz 110 weisen erfindungsgemäß eine höhere Lebensdauer auf. Durch den erfindungsgemäßen Brenner mit dem inneren Piloteinsatz 190 ist zudem eine Prallkühlung des Pilotkonus 200 möglich. Dies führt zu einer wesentlichen Kühllufteinsparung. Zudem stellt der definierte Einsatz einer Prallkühlung an besonders kritischen Stellen einer weiteren Erhöhung zur Lebensdauer der einzelnen Komponenten dar. Durch das verbesserte Montageverfahren wird die Montage/Demontage der Pilot-Konus Baugruppe erhöht. Auch die eigentliche Entkopplung zwischen Pilotkonus 200 und Trägereinsatz 110 trägt zur verbesserten Montage/Demontage beider Bauteile bei.The inventive method and the burner according to the invention with a thermally decoupled
Claims (10)
dadurch gekennzeichnet, dass der Pilotkonus (200) und der Trägereinsatz (110) thermisch entkoppelt sind.A burner comprising a pilot cone (200) and a carrier insert (110),
characterized in that the pilot cone (200) and the carrier insert (110) are thermally decoupled.
dadurch gekennzeichnet, dass zwischen Trägereinsatz (110) und Pilotkonus (200) ein innerer Piloteinsatz (190) vorgesehen ist.Burner according to claim 1,
characterized in that an inner pilot insert (190) is provided between the carrier insert (110) and the pilot cone (200).
dadurch gekennzeichnet, dass am inneren Piloteinsatz (190) Öffnungen (160) vorgesehen sind.Burner according to claim 2,
characterized in that at the inner pilot insert (190) openings (160) are provided.
dadurch gekennzeichnet, dass der Pilotkonus (200) mit dem inneren Piloteinsatz (190) verschweißt ist.Burner according to one of claims 2 to 3,
characterized in that the pilot cone (200) is welded to the inner pilot insert (190).
dadurch gekennzeichnet, dass der innere Piloteinsatz (190) mit dem Trägereinsatz (110) verschraubt ist.Burner according to one of claims 2 to 4,
characterized in that the inner pilot insert (190) is bolted to the carrier insert (110).
dadurch gekennzeichnet, dass zwischen Pilotkonus (200) und Trägereinsatz (110) ein definierter Spalt (180) vorgesehen ist.Burner according to one of the preceding claims,
characterized in that a defined gap (180) is provided between pilot cone (200) and carrier insert (110).
dadurch gekennzeichnet, dass der Pilotkonus (200) derart beabstandet angeordnet ist, dass ein definierter Spalt zwischen Pilotkonus (200) und Trägereinsatz (110) vorgesehen ist, welcher im Betrieb durch die thermische Expansion in wesentlichen geschlossen wird.Operating method for increasing the life of a burner, comprising a pilot cone (200) and a carrier insert (110),
characterized in that the pilot cone (200) is arranged at a distance such that a defined gap is provided between the pilot cone (200) and the carrier insert (110), which in operation is essentially closed by the thermal expansion.
dadurch gekennzeichnet, dass zwischen Pilotkonus (200) und einen Trägereinsatz (110) ein innerer Piloteinsatz (190) mit Öffnungen (160) vorhanden ist, mittels welchem der Pilotkonus (200) prallluftgekühlt wird.Operating method according to claim 8,
characterized in that between the pilot cone (200) and a carrier insert (110) an inner pilot insert (190) with openings (160) is present, by means of which the pilot cone (200) is impingement air cooled.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09161187A EP2256413A1 (en) | 2009-05-27 | 2009-05-27 | Burner, operating method and fitting method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09161187A EP2256413A1 (en) | 2009-05-27 | 2009-05-27 | Burner, operating method and fitting method |
Publications (1)
Publication Number | Publication Date |
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EP2256413A1 true EP2256413A1 (en) | 2010-12-01 |
Family
ID=41139151
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09161187A Withdrawn EP2256413A1 (en) | 2009-05-27 | 2009-05-27 | Burner, operating method and fitting method |
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EP (1) | EP2256413A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100300104A1 (en) * | 2009-05-27 | 2010-12-02 | Boettcher Andreas | Burner, operating method and assembly method |
FR2998038A1 (en) * | 2012-11-09 | 2014-05-16 | Snecma | COMBUSTION CHAMBER FOR A TURBOMACHINE |
EP3805642A1 (en) * | 2019-10-11 | 2021-04-14 | Siemens Aktiengesellschaft | Pilot conus cooling |
CN114754378A (en) * | 2022-06-13 | 2022-07-15 | 成都中科翼能科技有限公司 | Gas turbine combustor structure |
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US5024058A (en) * | 1989-12-08 | 1991-06-18 | Sundstrand Corporation | Hot gas generator |
EP0550218A1 (en) * | 1991-12-30 | 1993-07-07 | General Electric Company | Gas turbine combustors |
EP1001224A2 (en) * | 1998-11-12 | 2000-05-17 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US20010026911A1 (en) * | 2000-03-24 | 2001-10-04 | Neville Thomas B. | Premix burner with integral mixers and supplementary burner system |
WO2009005516A2 (en) * | 2007-01-23 | 2009-01-08 | Siemens Energy, Inc. | Anti-flashback features in gas turbine engine combustors |
-
2009
- 2009-05-27 EP EP09161187A patent/EP2256413A1/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5024058A (en) * | 1989-12-08 | 1991-06-18 | Sundstrand Corporation | Hot gas generator |
EP0550218A1 (en) * | 1991-12-30 | 1993-07-07 | General Electric Company | Gas turbine combustors |
EP1001224A2 (en) * | 1998-11-12 | 2000-05-17 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US20010026911A1 (en) * | 2000-03-24 | 2001-10-04 | Neville Thomas B. | Premix burner with integral mixers and supplementary burner system |
WO2009005516A2 (en) * | 2007-01-23 | 2009-01-08 | Siemens Energy, Inc. | Anti-flashback features in gas turbine engine combustors |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100300104A1 (en) * | 2009-05-27 | 2010-12-02 | Boettcher Andreas | Burner, operating method and assembly method |
US9127842B2 (en) * | 2009-05-27 | 2015-09-08 | Siemens Aktiengesellschaft | Burner, operating method and assembly method |
FR2998038A1 (en) * | 2012-11-09 | 2014-05-16 | Snecma | COMBUSTION CHAMBER FOR A TURBOMACHINE |
US9599344B2 (en) | 2012-11-09 | 2017-03-21 | Snecma | Combustion chamber for a turbine engine |
EP3805642A1 (en) * | 2019-10-11 | 2021-04-14 | Siemens Aktiengesellschaft | Pilot conus cooling |
CN114754378A (en) * | 2022-06-13 | 2022-07-15 | 成都中科翼能科技有限公司 | Gas turbine combustor structure |
CN114754378B (en) * | 2022-06-13 | 2022-08-19 | 成都中科翼能科技有限公司 | Gas turbine combustor structure |
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