EP2808611B1 - Injector for introducing a fuel-air mixture into a combustion chamber - Google Patents
Injector for introducing a fuel-air mixture into a combustion chamber Download PDFInfo
- Publication number
- EP2808611B1 EP2808611B1 EP13170048.6A EP13170048A EP2808611B1 EP 2808611 B1 EP2808611 B1 EP 2808611B1 EP 13170048 A EP13170048 A EP 13170048A EP 2808611 B1 EP2808611 B1 EP 2808611B1
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- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- injector
- fuel
- longitudinal axis
- air mixture
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- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/346—Feeding into different combustion zones for staged combustion
Definitions
- the present invention relates to an injector for introducing a fuel-air mixture into a combustion chamber, a combustion chamber and a gas turbine.
- Modern gas turbines should meet the requirements in terms of pollutant emissions and environmental friendliness in a wide operating range. The fulfillment of these requirements depends essentially on the combustion system used in the gas turbine.
- NOx nitrogen oxides
- To reduce emissions of nitrogen oxides (NOx) lean premix is used.
- high turbine inlet temperatures are sought to achieve a high efficiency, which are associated with high flame temperatures.
- the aforementioned premixed flames are susceptible to thermoacoustic instabilities due to the high thermal power density and the NOx emissions increase exponentially with increasing flame temperature.
- axial staging consists of a conventional burner that fires a primary combustion zone. This primary zone can in turn be internally graded like conventional burners and covers the load range up to today's firing temperatures. Downstream of the primary zone is followed by a secondary combustion zone. In this additional fuel is injected through an axially offset from the primary zone stage. This is then burned in a diffusion-like regime.
- the fuel may be diluted with inert components (steam, nitrogen, carbon dioxide) to greatly lower the stoichiometric combustion temperature, thereby suppressing NOx formation.
- inert components steam, nitrogen, carbon dioxide
- the US 2011/0067402 A1 discloses a gas turbine with a combustion chamber having a dual stage combustion concept.
- the combustor includes a combustor head end having a burner assembly, a combustor exit and a combustor wall, the combustor wall extending from the combustor head end to the combustor exit, and a primary zone and a secondary zone.
- the secondary zone is arranged in the main flow direction of the hot gas downstream of the primary zone.
- injectors opening into the secondary zone are arranged, which form a second axial stage of the combustion system.
- the invention has for its object to provide an injector for introducing a fuel-air mixture in a combustion chamber, a combustion chamber and a gas turbine with at least one such combustion chamber, with the / a reduction in emissions of nitrogen oxides (NOx) and low CO emissions can be achieved.
- NOx nitrogen oxides
- the first object is achieved by an injector according to claim 1
- the second object is achieved by a combustion chamber according to claim 8.
- the third object is achieved by a gas turbine according to claim 15.
- the injector according to the invention for introducing a fuel-air mixture into a combustion chamber comprises a longitudinal axis and a number of curved, ie not straight, in particular arcuate, flow channels.
- arcuate is "curved in the form of at least one arc", for example, also S-shaped curved, understood.
- Each flow channel comprises a fuel inlet opening, a number of air inlet openings and a fuel-air mixture outlet opening.
- the fuel inlet opening is connected to a fuel distributor.
- the fuel inlet opening may also have a central axis which runs perpendicular or parallel to the longitudinal axis of the injector.
- the fuel-air mixture outlet port has a central axis that is perpendicular to the longitudinal axis of the injector.
- the air inlet openings each have a central axis which runs parallel to the longitudinal axis of the injector.
- a fuel-air mixture generated in the flow channels can be introduced into a combustion chamber, for example into a secondary stage of a combustion chamber. Due to the curved, for example, also S-shaped curved shape of the flow channels a large mixing length is achieved on a small available space.
- the injector can be arranged on the combustion chamber such that its longitudinal axis extends substantially parallel to a longitudinal axis of the combustion chamber.
- the longitudinal axis of the injector may coincide with a longitudinal axis of the combustion chamber.
- the air inlet openings of a flow channel are arranged in at least one row. In this way, a continuous mixing of the fuel introduced into the flow channel through the fuel inlet opening with the air introduced into the flow channel through the air inlet openings is achieved.
- the air inlet openings may have a circular cross-section. In particular, they can be designed as bores.
- a number of air inlet openings may preferably extend in a spiral shape, for example spirally with respect to an axis parallel to the longitudinal axis of the injector.
- Each flow channel can in particular one at least have at least one row of the air inlet openings parallel to the center line of the flow channel.
- the fuel distributor can be designed annular.
- the fuel distributor may be arranged radially outside of the curved, in particular arcuate, flow channels, in particular with respect to the longitudinal axis of the injector.
- the fuel distributor can be arranged in the axial direction next to the arcuate flow channels.
- the curved, for example, arcuate, flow channels may have a curvature angle greater than 0 ° and less than 180 °, for example between 10 ° and 90 °, advantageously between 30 ° and 60 °.
- at least one of the curved, in particular arcuate, flow channels can have a curvature axis that runs parallel to the longitudinal axis of the injector.
- all the axes of curvature of the flow channels are parallel to the longitudinal axis of the injector.
- the injector may comprise two disks arranged substantially parallel to each other.
- the discs may comprise the side walls of the flow channels and the air inlet openings or in particular form the side walls of the flow channels.
- an annular fuel distributor can be firmly connected via the two disks arranged in parallel with a combustion chamber, for example with the liner of a combustion chamber or the combustion chamber wall.
- the air inlet openings may be spirally arranged in the disks in the form of air holes in several rows. Several side walls between the two discs can separate the individual flow channels or mixing channels.
- the fuel can be injected via several fuel inlet openings, for example in the form of bores, on the inside of the fuel distributor with respect to the longitudinal axis of the injector in the mixing channels.
- the air may be added perpendicular to and mixed with the fuel flow vertically through the spirally disposed air holes.
- the fuel-air mixture then passes into the combustion chamber of a combustion chamber through a plurality of openings, such as holes, and ignites there.
- the combustion chamber according to the invention comprises at least one previously described injector.
- the combustor may include a longitudinal axis, a combustor head end, a combustor exit, and a combustor wall extending from the combustor head end to the combustor exit. It may further include a primary zone and a secondary zone disposed in the main flow direction of the hot gas downstream of the primary zone.
- the at least one injector may be arranged in the region of the secondary zone on the combustion chamber wall such that the fuel-air mixture outlet openings open into the secondary zone. In this case, the injector can serve for introducing a fuel-air mixture into the secondary zone.
- the fuel-air mixture outlet ports may be spaced from each other along a circumferential line on the combustion chamber wall.
- the combustion chamber may include a liner region that includes the at least one injector.
- the liner region can connect to the primary zone in the main flow direction.
- a transition area may connect to the combustor exit.
- the at least one injector may be arranged at the liner area or be configured in one piece with the liner area.
- the liner region may comprise a longitudinal axis which coincides with the longitudinal axis of the injector.
- the longitudinal axis of the Injector can also run parallel to the longitudinal axis of the liner area.
- the liner region can only form a region of the combustion chamber or be designed as a separate component. It can be arranged between the primary zone and the combustion chamber outlet, for example in the region of the secondary zone.
- At least one injector according to the invention is arranged on the combustion chamber wall in the region of the secondary zone.
- a so-called “air-assisted axial stage” is realized.
- the combustion chamber may be a tube combustion chamber or an annular combustion chamber. At least one burner may be arranged at the end of the combustion chamber.
- the primary zone is determined by the area in which the fuel supplied via the burner is primarily burned within the combustion chamber.
- the secondary zone is characterized by the fact that in it the hot gas generated in the primary zone is further burned out as completely as possible.
- the secondary zone can in principle be arranged at any desired position between the primary zone and the combustion chamber exit.
- the airborne axial stage itself has several advantages. By premixing fuel and air outside the combustion chamber as with conventional burner technology, the resulting peak temperatures and thus NOx emissions can be reduced. Lower residence times in the secondary zone and turbine entry continue to result in lower overall NOx emissions. In addition, no additional media are needed, but an operation takes place only with the originating from the compressor outlet air, which with fuel in the axial stage to a mixture is processed. Therefore, the resulting system is robust and stable available.
- the fuel supply to the axial stage is completely shut off and then behaves like an air bypass. This allows the primary zone to operate at very low loads with a high local flame temperature, which ensures good burnout and low CO emissions.
- the airborne axial stage therefore equally serves to expand the operating range of the combustion system to lower and higher loads.
- the present invention also has the following special advantages: Due to the curved, in particular spiral-shaped arrangement, a long mixing length can be achieved in the flow channels of the injector despite its compact design. This achieves a high premix quality on a small available space.
- the swirl generation provides for the generation of additional gradients and shear layers and thus for a better mixing with the main flow.
- a smoother turbine entry profile reduces emissions.
- a simple and inexpensive construction of the guide vanes of the first turbine stage (TLe 1) is made possible.
- the present invention opens up great potential for saving cooling air and possibly saving potential by dispensing with the vanes of the first turbine stage (TLe 1).
- the gas turbine according to the invention comprises a combustion chamber described above. It has the same characteristics and advantages as the combustion chamber described above.
- FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
- the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
- an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
- a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
- the combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
- annular annular hot gas channel 111 for example.
- turbine stages 112 connected in series form the turbine 108.
- Each turbine stage 112 is formed, for example, from two blade rings.
- the hot gas channel 111 of a row of guide vanes 115 is followed by a row 125 formed of rotor blades 120.
- the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
- air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
- the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
- the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
- the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
- the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
- the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
- the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
- iron, nickel or cobalt-based superalloys are used as the material for the components, in particular for the turbine blades 120, 130 and components of the combustion chamber 110.
- the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
- the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
- the FIG. 2 schematically shows a combustion chamber 110 of a gas turbine.
- the combustor 110 shown is configured as a so-called annular combustor in which a plurality of burners 107 circumferentially disposed about a longitudinal axis of the combustor 102 open into a common combustor chamber 154 which generates flames.
- the combustion chamber 110 is configured in its entirety as an annular structure which is positioned around the longitudinal axis 102.
- the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
- the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
- FIG. 3 schematically shows a part of a combustion chamber in a partially perspective and partially sectioned view.
- the combustion chamber comprises a combustion chamber wall 1 and a combustion chamber outlet 6.
- the main flow direction of the hot gas in the combustion chamber during operation of the combustion chamber is indicated by an arrow 3.
- the combustion chamber further comprises a primary zone 4, in which the fuel introduced from the burner into the combustion chamber is burned.
- a secondary zone 5 adjoins the primary zone in the direction of flow 3.
- the hot gas from the primary zone 4 is further burned off. This is done by additionally introducing a fuel-air mixture 14 in the secondary zone 5 by means of injectors. 8
- the injectors 8 comprise an air supply 13 and an outlet 9 opening into the combustion chamber. Furthermore, a fuel nozzle 10 is arranged in the interior of each injector 8. The fuel nozzle 10 is connected to a fuel distributor 11, preferably an annular fuel distributor 11. With the help of the fuel nozzle 10, fuel is injected into the interior of the injector 8 and in this way generates a fuel-air mixture in the interior of the injector 8. The fuel-air mixture thus produced is then injected through the injector outlet or the injection opening 9 into the combustion chamber in the region of the secondary zone 5.
- a liner region 7 and a transition region 25 which in the FIG. 3 are each designed as separate components.
- a sealing ring 12 is arranged between the primary zone 4 and the liner area 7 between the primary zone 4 and the liner area 7 .
- at least one sealing ring 12 is also arranged between the liner region 7 and the transitional component 25.
- the injectors 8 are connected to the liner area 7.
- the injector or injection ports 9 open in the region of the liner region 7 in the secondary zone 5 of the combustion chamber.
- FIG. 4 shows a section of the already in the FIG. 3 partially shown combustion chamber in perspective and sectional view.
- a fuel supply 15 is shown, which supplies the fuel distributor 11 with fuel.
- FIG. 5 schematically shows the liner region with an injector 28 according to the invention, which is referred to below as Spiralinjektor, in a perspective view.
- the liner region 7 comprises an outer surface 32 on which the spiral injector 28 is arranged.
- the spiral injector 28 comprises outlet openings 9, through which the fuel-air mixture generated within the spiral injector 28 is introduced into the interior of the combustion chamber.
- the Outlet openings 9 a rectangular, for example square, shape. Alternatively, they may also have a circular cross-section.
- the spiral injector 28 includes an annular fuel manifold 41 disposed about the outer surface 32 of the liner region 7.
- the annular fuel distributor 41 forms in the embodiment variant shown here at the same time with respect to the longitudinal axis or central axis 44 of the liner region 7 radially outwardly disposed portion of the Spiralinjektors 28.
- the central axis or longitudinal axis 44 of the liner region 7 corresponds to the central axis or longitudinal axis of the injector 28 according to the invention.
- the annular fuel distributor 41 comprises at least one fuel supply 45.
- two fuel supply means 45 are arranged opposite each other with respect to the longitudinal axis 44 of the injector.
- the spiral injector 28 further comprises flow channels or injector channels 48 arranged between the fuel distributor 41 and the outer surface 32 (see FIGS. 6 and 7 ).
- the injector channels 48 are arranged in a disc-shaped region which connects the outer surface 32 of the liner region 7 to the annular fuel distributor 41.
- the air holes 42 are preferably provided on both sides of the spiral injector, that is, on the upstream and downstream surfaces 50 with respect to the main flow direction 3.
- the air holes 42 are arranged side by side in individual rows.
- Each row of air holes is assigned to an injector channel 48.
- the respective injector channel 48 and corresponding to the respective air hole row has a curved, preferably spiral shape leading to the central axis 44 towards.
- the air inlet openings or air bores 42 each have a central axis 54, which runs parallel to the longitudinal axis 44 of the injector.
- FIGS. 6 and 7 In each case, sections through partial regions of a spiral injector 28 according to the invention are shown in a partially perspective view. It runs in the FIG. 6 shown section perpendicular to the longitudinal axis 44 of the injector and in the FIG. 7 shown section parallel to the longitudinal axis 44th
- the fuel conducted through the annular fuel distributor 41 to the injector channels 48 is introduced into the injector channels 48 in the flow direction 46. Air is supplied to the injector channels 48 via the air bores 42 at the same time. As a result, a fuel-air mixture is generated in the interior of the injector channels 48, which is then introduced through the outlet openings 9 into the combustion chamber.
- the individual injector channels 48 are delimited from each other by side walls 49.
- the spiral injector 28 is perpendicular to the liner region 7, that is perpendicular to the central axis 44 of the liner region 7, installed, wherein the longitudinal axis 44 of the injector, which can also be referred to the central axis 44 of the injector, in the illustrated embodiment with the central axis of the injector Liners coincides.
- the annular fuel distributor 41 is fixedly connected to the liner area 7, for example, via two disks arranged in parallel. In these discs, the air holes 42 are arranged spirally or arcuately in a plurality of rows. A plurality of side walls 49 between the two discs separate different mixing channels or injector channels 48 from each other.
- the fuel is through several openings, such as holes 43, on the inside of the fuel distributor 41 in the mixing channels 48th injected.
- the air is added and mixed vertically through the spirally arranged air holes 42 to the fuel flow 46.
- the fuel-air mixture then passes into the combustion chamber through a plurality of openings 9, for example holes, in the liner area 7 and ignites there.
- the fuel inlet openings 43 each have a central axis 55, which extends perpendicularly, in particular tangentially, to the central axis 44 of the injector.
- FIG. 8 shows a further embodiment variant, in which the fuel distributor 41 is arranged in relation to the longitudinal axis 44 of the injector 8 in the axial direction adjacent to the arcuate flow channels 48.
- the direction of flow of the fuel is identified by the reference numeral 51.
- the direction of flow of the air is indicated by the reference numeral 52.
- FIG. 9 schematically shows a section through a portion of an injector according to the invention perpendicular to the central axis.
- the injector 48 are configured S-shaped.
- the air inlet openings 42 are arranged in an S shape.
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Description
Die vorliegende Erfindung betrifft einen Injektor zum Einbringen eines Brennstoff-Luft-Gemisches in eine Brennkammer, eine Brennkammer und eine Gasturbine.The present invention relates to an injector for introducing a fuel-air mixture into a combustion chamber, a combustion chamber and a gas turbine.
Moderne Gasturbinen sollen in einem weiten Betriebsbereich den Anforderungen bezüglich Schadstoffemissionen und Umweltfreundlichkeit genügen. Die Erfüllung dieser Anforderungen hängt wesentlich von dem in der Gasturbine eingesetzten Verbrennungssystem ab. Zur Reduktion der Emissionen von Stickoxiden (NOx) wird magere Vormischung verwendet. Dabei werden zur Erzielung eines hohen Wirkungsgrades hohe Turbineneintrittstemperaturen angestrebt, die mit hohen Flammentemperaturen einhergehen. Hier sind die erwähnten Vormischflammen aufgrund der hohen thermischen Leistungsdichte anfällig für thermoakustische Instabilitäten und die NOx-Emissionen nehmen mit steigender Flammentemperatur exponentiell zu.Modern gas turbines should meet the requirements in terms of pollutant emissions and environmental friendliness in a wide operating range. The fulfillment of these requirements depends essentially on the combustion system used in the gas turbine. To reduce emissions of nitrogen oxides (NOx) lean premix is used. In this case, high turbine inlet temperatures are sought to achieve a high efficiency, which are associated with high flame temperatures. Here, the aforementioned premixed flames are susceptible to thermoacoustic instabilities due to the high thermal power density and the NOx emissions increase exponentially with increasing flame temperature.
Auf der anderen Seite ist ein Betrieb der Gasturbine bei möglichst niedrigen Lasten und Flammentemperaturen notwendig, um den Anforderungen der Kraftwerksbetreiber gerecht zu werden. Hier wird der Betriebsbereich nach unten hin durch die bei unvollständigem Ausbrand entstehenden Kohlenmonoxidemissionen (CO) begrenzt. Daher ist es wünschenswert, den Betriebsbereich des Verbrennungssystems in beide Richtungen zu erweitern.On the other hand, operation of the gas turbine at the lowest possible loads and flame temperatures is necessary to meet the requirements of power plant operators. Here, the operating range is limited at the bottom by the resulting incomplete burnout carbon monoxide (CO) emissions. Therefore, it is desirable to expand the operating range of the combustion system in both directions.
Zur Erweiterung des Betriebsbereiches bei bestehenden Verbrennungssystemen wurde beispielsweise durch brennerinterne Brennstoffstufung, effiziente Vormischeinrichtungen, Reduktion von Kühlluft und gestufte Verbrennungskonzepte eine Optimierung des Systems für die heutigen Anforderungen vorgenommen. Die "axial staging" genannte gestufte Verbrennungstechnologie besteht aus einem konventionellen Brenner, der eine primäre Verbrennungszone befeuert. Diese Primärzone kann wiederum wie konventionelle Brenner intern gestuft sein und deckt den Lastbereich bis zu heutigen Feuerungstemperaturen ab. Stromab der Primärzone schließt sich eine sekundäre Verbrennungszone an. In diese wird durch eine axial gegenüber der Primärzone versetzte Stufe zusätzlicher Brennstoff eingedüst. Dieser wird dann in einem diffusionsartigen Regime verbrannt. Der Brennstoff kann mit Inertkomponenten (Dampf, Stickstoff, Kohlendioxid) verdünnt werden, um die stöchiometrische Verbrennungstemperatur stark abzusenken und damit die NOx-Bildung unterdrückt. Gleichzeitig wird durch die Verteilung der Wärmefreisetzung über den gesamten zur Verfügung stehenden Brennraum die Neigung des Verbrennungssystems zu thermoakustischen Instabilitäten verringert.To expand the operating range of existing combustion systems was, for example, by burner internal Fuel staging, efficient premixing, reduction of cooling air and staged combustion concepts made an optimization of the system for today's requirements. The staged combustion technology called "axial staging" consists of a conventional burner that fires a primary combustion zone. This primary zone can in turn be internally graded like conventional burners and covers the load range up to today's firing temperatures. Downstream of the primary zone is followed by a secondary combustion zone. In this additional fuel is injected through an axially offset from the primary zone stage. This is then burned in a diffusion-like regime. The fuel may be diluted with inert components (steam, nitrogen, carbon dioxide) to greatly lower the stoichiometric combustion temperature, thereby suppressing NOx formation. At the same time, the distribution of the heat release over the entire available combustion chamber reduces the inclination of the combustion system to thermoacoustic instabilities.
Die für einen sicheren Betrieb innerhalb der gewährleisteten Emissionsgrenzen benötigten Verdünnungsmedien müssen aus separaten Prozessen zur Verfügung gestellt werden, was zu etlichen Nachteilen führt. Erstens steigt die Komplexität des Gesamtkraftwerks im Sinne höherer Investitionskosten. Zweitens benötigen diese separaten Prozesse ihrerseits Energie, so dass der Gesamtwirkungsgrad beeinträchtigt wird. Drittens sinkt die Verfügbarkeit des Kraftwerkes, da diese Prozesse eine gewisse Ausfallswahrscheinlichkeit besitzen, welche zu der des konventionellen Kraftwerkes hinzugerechnet werden muss. Aus diesem Grund ist es auch bekannt, den Brennstoff in der zweiten axialen Stufe ohne Inertkomponenten in Form eines Luft/Brennstoff Gemisches in die Sekundärzone einzubringen ("fuel only").The dilution media required for safe operation within the guaranteed emission limits must be made available from separate processes, which leads to several disadvantages. First, the complexity of the entire power plant increases in terms of higher investment costs. Second, these separate processes in turn require energy so that overall efficiency is compromised. Thirdly, the availability of the power plant decreases because these processes have a certain probability of failure, which must be added to that of the conventional power plant. For this reason, it is also known to introduce the fuel in the second axial stage without inert components in the form of an air / fuel mixture in the secondary zone ("fuel only").
Diesbezüglicher und weiterer Stand der Technik ist in den Dokumenten
Die
Der Erfindung liegt die Aufgabe zugrunde, einen Injektor zum Einbringen eines Brennstoff-Luft-Gemisches in eine Brennkammer, eine Brennkammer sowie eine Gasturbine mit mindestens einer derartigen Brennkammer zur Verfügung zu stellen, mit dem/der eine Reduzierung der Emissionen von Stickoxiden (NOx) und niedrige CO-Emissionen erreicht werden kann.The invention has for its object to provide an injector for introducing a fuel-air mixture in a combustion chamber, a combustion chamber and a gas turbine with at least one such combustion chamber, with the / a reduction in emissions of nitrogen oxides (NOx) and low CO emissions can be achieved.
Die erste Aufgabe wird durch einen Injektor nach Anspruch 1 gelöst, die zweite Aufgabe wird durch eine Brennkammer nach Anspruch 8 gelöst. Die dritte Aufgabe wird durch eine Gasturbine nach Anspruch 15 gelöst. Die abhängigen Ansprüche enthalten weitere vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by an injector according to
Der erfindungsgemäße Injektor zum Einbringen eines Brennstoff-Luft-Gemisches in eine Brennkammer umfasst eine Längsachse und eine Anzahl gekrümmter, also nicht gerader, insbesondere bogenförmiger, Strömungskanäle. Unter dem Begriff "bogenförmig" wird dabei "in der Form mindestens eines Bogens gekrümmt", beispielsweise auch S-förmig gekrümmt, verstanden. Jeder Strömungskanal umfasst eine Brennstoffeinlassöffnung, eine Anzahl Lufteinlassöffnungen und eine Brennstoff-Luft-Gemisch-Auslassöffnung. Dabei ist die Brennstoffeinlassöffnung mit einem Brennstoffverteiler verbunden. Die Brennstoffeinlassöffnung kann zudem eine Mittelachse aufweisen, die senkrecht oder parallel zur Längsachse des Injektors verläuft. Die Brennstoff-Luft-Gemisch-Auslassöffnung weist eine Mittelachse auf, die senkrecht zur Längsachse des Injektors verläuft. Die Lufteinlassöffnungen weisen jeweils eine Mittelachse auf, die parallel zur Längsachse des Injektors verläuft.The injector according to the invention for introducing a fuel-air mixture into a combustion chamber comprises a longitudinal axis and a number of curved, ie not straight, in particular arcuate, flow channels. The term "arcuate" is "curved in the form of at least one arc", for example, also S-shaped curved, understood. Each flow channel comprises a fuel inlet opening, a number of air inlet openings and a fuel-air mixture outlet opening. In this case, the fuel inlet opening is connected to a fuel distributor. The fuel inlet opening may also have a central axis which runs perpendicular or parallel to the longitudinal axis of the injector. The fuel-air mixture outlet port has a central axis that is perpendicular to the longitudinal axis of the injector. The air inlet openings each have a central axis which runs parallel to the longitudinal axis of the injector.
Durch die Brennstoff-Luft-Gemisch-Auslassöffnungen kann ein in den Strömungskanälen erzeugtes Brennstoff-Luft-Gemisch in eine Brennkammer, beispielsweise in eine Sekundärstufe einer Brennkammer, eingebracht werden. Durch die gebogene, beispielsweise auch S-förmig gebogene, Form der Strömungskanäle wird eine große Mischlänge auf kleinem zur Verfügung stehendem Raum erreicht.Through the fuel-air mixture outlet openings, a fuel-air mixture generated in the flow channels can be introduced into a combustion chamber, for example into a secondary stage of a combustion chamber. Due to the curved, for example, also S-shaped curved shape of the flow channels a large mixing length is achieved on a small available space.
Vorteilhafterweise kann der Injektor derart an der Brennkammer anordenbar sein, dass seine Längsachse im Wesentlichen parallel zu einer Längsachse der Brennkammer verläuft. Insbesondere kann die Längsachse des Injektors mit einer Längsachse der Brennkammer zusammenfallen.Advantageously, the injector can be arranged on the combustion chamber such that its longitudinal axis extends substantially parallel to a longitudinal axis of the combustion chamber. In particular, the longitudinal axis of the injector may coincide with a longitudinal axis of the combustion chamber.
Vorteilhafterweise sind die Lufteinlassöffnungen eines Strömungskanals in mindestens einer Reihe angeordnet. Auf diese Weise wird eine kontinuierliche Mischung des durch die Brennstoffeinlassöffnung in den Strömungskanal eingebrachten Brennstoffes mit der durch die Lufteinlassöffnungen in den Strömungskanal eingebrachten Luft erzielt.Advantageously, the air inlet openings of a flow channel are arranged in at least one row. In this way, a continuous mixing of the fuel introduced into the flow channel through the fuel inlet opening with the air introduced into the flow channel through the air inlet openings is achieved.
Die Lufteinlassöffnungen können einen kreisförmigen Querschnitt haben. Sie können insbesondere als Bohrungen ausgestaltet sein. Eine Reihe Lufteinlassöffnungen kann vorzugsweise spiralförmig verlaufen, beispielsweise spiralförmig in Bezug auf eine zur Längsachse des Injektors parallel verlaufende Achse. Jeder Strömungskanal kann insbesondere eine zumindest teilweise gekrümmte oder bogenförmig verlaufende Mittellinie aufweisen und die mindestens eine Reihe der Lufteinlassöffnungen kann parallel zu der Mittellinie des Strömungskanals verlaufen.The air inlet openings may have a circular cross-section. In particular, they can be designed as bores. A number of air inlet openings may preferably extend in a spiral shape, for example spirally with respect to an axis parallel to the longitudinal axis of the injector. Each flow channel can in particular one at least have at least one row of the air inlet openings parallel to the center line of the flow channel.
Weiterhin kann der Brennstoffverteiler ringförmig ausgestaltet sein. Der Brennstoffverteiler kann insbesondere bezüglich der Längsachse des Injektors radial außerhalb der gekrümmten, insbesondere bogenförmigen, Strömungskanäle angeordnet sein. Alternativ dazu, kann der Brennstoffverteiler in axialer Richtung neben den bogenförmigen Strömungskanälen angeordnet sein.Furthermore, the fuel distributor can be designed annular. The fuel distributor may be arranged radially outside of the curved, in particular arcuate, flow channels, in particular with respect to the longitudinal axis of the injector. Alternatively, the fuel distributor can be arranged in the axial direction next to the arcuate flow channels.
Die gekrümmten, beispielsweise bogenförmigen, Strömungskanäle können einen Krümmungswinkel größer als 0° und kleiner als 180°, beispielsweise zwischen 10° und 90°, vorteilhafterweise zwischen 30° und 60°, aufweisen. Zudem kann mindestens einer der gekrümmten, insbesondere bogenförmigen, Strömungskanäle eine Krümmungsachse aufweisen, die parallel zur Längsachse des Injektors verläuft. Vorzugsweise verlaufen alle Krümmungsachsen der Strömungskanäle parallel zur Längsachse des Injektors.The curved, for example, arcuate, flow channels may have a curvature angle greater than 0 ° and less than 180 °, for example between 10 ° and 90 °, advantageously between 30 ° and 60 °. In addition, at least one of the curved, in particular arcuate, flow channels can have a curvature axis that runs parallel to the longitudinal axis of the injector. Preferably, all the axes of curvature of the flow channels are parallel to the longitudinal axis of the injector.
Der Injektor kann zum Beispiel zwei im Wesentlichen parallel zueinander angeordnete Scheiben umfassen. Dabei können die Scheiben die Seitenwände der Strömungskanäle und die Lufteinlassöffnungen umfassen oder insbesondere die Seitenwände der Strömungskanäle bilden. Zudem kann ein ringförmiger Brennstoffverteiler über die zwei parallel angeordneten Scheiben mit einer Brennkammer, beispielsweise mit dem Liner einer Brennkammer bzw. der Brennraumwand, fest verbunden sein. Die Lufteinlassöffnungen können in den Scheiben in Form von Luftbohrungen spiralförmig in mehreren Reihen angeordnet sein. Mehrere Seitenwände zwischen den beiden Scheiben können die einzelnen Strömungskanäle oder Mischkanäle voneinander trennen.For example, the injector may comprise two disks arranged substantially parallel to each other. In this case, the discs may comprise the side walls of the flow channels and the air inlet openings or in particular form the side walls of the flow channels. In addition, an annular fuel distributor can be firmly connected via the two disks arranged in parallel with a combustion chamber, for example with the liner of a combustion chamber or the combustion chamber wall. The air inlet openings may be spirally arranged in the disks in the form of air holes in several rows. Several side walls between the two discs can separate the individual flow channels or mixing channels.
Der Brennstoff kann über mehrere Brennstoffeinlassöffnungen, beispielsweise in Form von Bohrungen, auf der Innenseite des Brennstoffverteilers in Bezug auf die Längsachse des Injektors in die Mischkanäle eingedüst werden. Die Luft kann senkrecht durch die spiralförmig angeordneten Luftbohrungen zu der Brennstoffströmung hinzugegeben und mit dieser vermischt werden. Das Brennstoff-Luft-Gemisch gelangt dann in den Brennraum einer Brennkammer durch mehrere Öffnungen, beispielsweise Bohrungen, und entzündet sich dort.The fuel can be injected via several fuel inlet openings, for example in the form of bores, on the inside of the fuel distributor with respect to the longitudinal axis of the injector in the mixing channels. The air may be added perpendicular to and mixed with the fuel flow vertically through the spirally disposed air holes. The fuel-air mixture then passes into the combustion chamber of a combustion chamber through a plurality of openings, such as holes, and ignites there.
Die erfindungsgemäße Brennkammer umfasst mindestens einen zuvor beschriebenen Injektor. Die Brennkammer kann eine Längsachse, ein Brennkammerkopfende, einen Brennkammerausgang und eine Brennkammerwand, die sich vom Brennkammerkopfende zum Brennkammerausgang erstreckt, umfassen. Sie kann zudem eine Primärzone und eine Sekundärzone, die in Hauptströmungsrichtung des Heißgases stromabwärts der Primärzone angeordnet ist, umfassen. Der mindestens eine Injektor kann im Bereich der Sekundärzone derart an der Brennkammerwand angeordnet sein, dass die Brennstoff-Luft-Gemisch-Auslassöffnungen in die Sekundärzone münden. Dabei kann der Injektor zum Einbringen eines Brennstoff-Luft-Gemisches in die Sekundärzone dienen.The combustion chamber according to the invention comprises at least one previously described injector. The combustor may include a longitudinal axis, a combustor head end, a combustor exit, and a combustor wall extending from the combustor head end to the combustor exit. It may further include a primary zone and a secondary zone disposed in the main flow direction of the hot gas downstream of the primary zone. The at least one injector may be arranged in the region of the secondary zone on the combustion chamber wall such that the fuel-air mixture outlet openings open into the secondary zone. In this case, the injector can serve for introducing a fuel-air mixture into the secondary zone.
Die Brennstoff-Luft-Gemisch-Auslassöffnungen können voneinander beabstandet entlang einer Umfangslinie an der Brennkammerwand angeordnet sein.The fuel-air mixture outlet ports may be spaced from each other along a circumferential line on the combustion chamber wall.
Weiterhin kann die Brennkammer einen Liner-Bereich umfassen, der den mindestens einen Injektor umfasst. Der Liner-Bereich kann sich in Hauptströmungsrichtung an die Primärzone anschließen. An den Liner-Bereich kann sich ein Übergangsbereich zum Brennkammerausgang anschließen. Der mindestens eine Injektor kann an dem Liner-Bereich angeordnet sein oder einstückig mit dem Liner-Bereich ausgestaltet sein. Zudem kann der Liner-Bereich eine Längsachse umfassen, die mit der Längsachse des Injektors zusammenfällt. Die Längsachse des Injektors kann auch parallel zur Längsachse des Liner-Bereichs verlaufen.Furthermore, the combustion chamber may include a liner region that includes the at least one injector. The liner region can connect to the primary zone in the main flow direction. At the liner area, a transition area may connect to the combustor exit. The at least one injector may be arranged at the liner area or be configured in one piece with the liner area. In addition, the liner region may comprise a longitudinal axis which coincides with the longitudinal axis of the injector. The longitudinal axis of the Injector can also run parallel to the longitudinal axis of the liner area.
Der Liner-Bereich kann lediglich einen Bereich der Brennkammer bilden oder als separates Bauteil ausgestaltet sein. Er kann zwischen der Primärzone und dem Brennkammerausgang angeordnet sein, beispielsweise im Bereich der Sekundärzone.The liner region can only form a region of the combustion chamber or be designed as a separate component. It can be arranged between the primary zone and the combustion chamber outlet, for example in the region of the secondary zone.
Vorzugsweise ist mindestens ein erfindungsgemäßer Injektor an der Brennkammerwand im Bereich der Sekundärzone angeordnet. Durch die kombinierte Eindüsung von Luft und Brennstoff in die Sekundärzone wird eine sogenannte "luftgestützte Axialstufe" realisiert.Preferably, at least one injector according to the invention is arranged on the combustion chamber wall in the region of the secondary zone. Through the combined injection of air and fuel into the secondary zone, a so-called "air-assisted axial stage" is realized.
Bei der Brennkammer kann es sich um eine Rohrbrennkammer oder eine Ringbrennkammer handeln. An dem Brennkammerkopfende kann mindestens ein Brenner angeordnet sein.The combustion chamber may be a tube combustion chamber or an annular combustion chamber. At least one burner may be arranged at the end of the combustion chamber.
Grundsätzlich wird die Primärzone durch den Bereich bestimmt, in welchem innerhalb der Brennkammer der über den Brenner zugeführte Brennstoff primär verbrannt wird. Die Sekundärzone zeichnet sich dadurch aus, dass in ihr das in der Primärzone erzeugte Heißgas weiter, möglichst vollständig, ausgebrannt wird. Dabei kann die Sekundärzone grundsätzlich an jeder beliebigen Position zwischen der Primärzone und dem Brennkammerausgang angeordnet sein.In principle, the primary zone is determined by the area in which the fuel supplied via the burner is primarily burned within the combustion chamber. The secondary zone is characterized by the fact that in it the hot gas generated in the primary zone is further burned out as completely as possible. In this case, the secondary zone can in principle be arranged at any desired position between the primary zone and the combustion chamber exit.
Die luftgestützte Axialstufe an sich hat bereits mehrere Vorteile. Durch ein Vormischen von Brennstoff und Luft außerhalb des Brennraums wie bei konventioneller Brennertechnologie können die entstehenden Spitzentemperaturen und damit die NOx-Emissionen verringert werden. Durch die niedrigeren Verweilzeiten in der Sekundärzone und bis zum Turbineneintritt ergeben sich weiterhin niedrigere Gesamt-NOx-Emissionen. Es werden zudem keine zusätzlichen Medien benötigt, sondern ein Betrieb erfolgt nur mit der vom Verdichteraustritt stammenden Luft, welche mit Brennstoff in der axialen Stufe zu einem Gemisch aufbereitet wird. Daher ist das entstehende System robust und stabil verfügbar.The airborne axial stage itself has several advantages. By premixing fuel and air outside the combustion chamber as with conventional burner technology, the resulting peak temperatures and thus NOx emissions can be reduced. Lower residence times in the secondary zone and turbine entry continue to result in lower overall NOx emissions. In addition, no additional media are needed, but an operation takes place only with the originating from the compressor outlet air, which with fuel in the axial stage to a mixture is processed. Therefore, the resulting system is robust and stable available.
Weiterhin kann durch eine geeignete Fahrweise die Beaufschlagung der Axialstufe mit Brennstoff erst bei relativ hohen Lasten erfolgen. Bei niedrigeren Lasten wird die Brennstoffzufuhr zur axialen Stufe komplett abgeschaltet und diese verhält sich dann wie ein Luftbypass. Dadurch kann die Primärzone selbst bei sehr tiefen Lasten mit einer hohen lokalen Flammentemperatur betrieben werden, welche für einen guten Ausbrand und entsprechend niedrige CO-Emissionen sorgt. Die luftgestützte Axialstufe dient daher gleichermaßen einer Erweiterung des Betriebsbereiches des Verbrennungssystems zu niedrigeren und höheren Lasten.Furthermore, can be done by a suitable driving the admission of the axial stage with fuel only at relatively high loads. At lower loads, the fuel supply to the axial stage is completely shut off and then behaves like an air bypass. This allows the primary zone to operate at very low loads with a high local flame temperature, which ensures good burnout and low CO emissions. The airborne axial stage therefore equally serves to expand the operating range of the combustion system to lower and higher loads.
Die vorliegende Erfindung hat darüber hinaus folgende spezielle Vorteile: Durch die gekrümmte, insbesondere spiralförmige Anordnung kann eine lange Mischlänge in den Strömungskanälen des Injektors trotz kompakter Bauweise erzielt werden. Dabei wird eine hohe Vormischgüte auf kleinem zur Verfügung stehendem Raum erreicht. Die Drallerzeugung sorgt für die Generierung zusätzlicher Gradienten und Scherschichten und somit für eine bessere Durchmischung mit der Hauptströmung. Durch ein gleichmäßigeres Turbineneintrittsprofil werden Emissionen gesenkt. Weiterhin wird eine einfache und kostengünstige Bauweise der Leitschaufeln der ersten Turbinenstufe (TLe 1) ermöglicht. Darüber hinaus eröffnet die vorliegende Erfindung großes Potenzial für eine Kühllufteinsparung und gegebenenfalls Sparpotenzial durch Verzicht auf die Leitschaufeln der ersten Turbinenstufe (TLe 1).The present invention also has the following special advantages: Due to the curved, in particular spiral-shaped arrangement, a long mixing length can be achieved in the flow channels of the injector despite its compact design. This achieves a high premix quality on a small available space. The swirl generation provides for the generation of additional gradients and shear layers and thus for a better mixing with the main flow. A smoother turbine entry profile reduces emissions. Furthermore, a simple and inexpensive construction of the guide vanes of the first turbine stage (TLe 1) is made possible. In addition, the present invention opens up great potential for saving cooling air and possibly saving potential by dispensing with the vanes of the first turbine stage (TLe 1).
Die erfindungsgemäße Gasturbine umfasst eine zuvor beschriebene Brennkammer. Sie hat dieselben Eigenschaften und Vorteile wie die zuvor beschriebene Brennkammer.The gas turbine according to the invention comprises a combustion chamber described above. It has the same characteristics and advantages as the combustion chamber described above.
Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung werden im Folgenden anhand von Ausführungsbeispielen unter Bezugnahme auf die beigefügten Figuren näher beschrieben. Die Ausführungsbeispiele schränken den durch die Patentansprüche bestimmten Schutzbereich der vorliegenden Erfindung nicht ein. Alle beschriebenen Merkmale sind dabei sowohl einzeln als auch in beliebiger Kombination miteinander vorteilhaft.
Figur 1- zeigt beispielhaft eine Gasturbine in einem Längsteilschnitt;
- Figur 2
- zeigt schematisch eine Ringbrennkammer einer Gasturbine;
Figur 3- zeigt schematisch einen Teil einer Rohrbrennkammer in einer teilweise perspektivischen und teilweise geschnittenen Ansicht;
Figur 4- zeigt einen Ausschnitt der bereits in
der Figur 3 teilweise gezeigten Brennkammer in perspektivischer und geschnittener Ansicht; Figur 5- zeigt schematisch den Liner-Bereich mit einem erfindungsgemäßen Injektor in perspektivischer Ansicht;
Figur 6- zeigt schematisch einen Schnitt durch einen Teilbereich eines erfindungsgemäßen Injektors in teilweise perspektivischer Ansicht senkrecht zur Längsachse des Injektors;
Figur 7- zeigt schematisch einen Schnitt durch einen Teilbereich eines erfindungsgemäßen Injektors in teilweise perspektivischer Ansicht parallel zur Längsachse des Injektors;
Figur 8- zeigt schematisch einen Teilbereich einer alternativen Ausgestaltung eines erfindungsgemäßen Injektors;
Figur 9- zeigt schematisch einen Schnitt durch einen Teilbereich eines erfindungsgemäßen Injektors senkrecht zur Längsachse des Injektors.
- FIG. 1
- shows by way of example a gas turbine in a longitudinal partial section;
- FIG. 2
- schematically shows an annular combustion chamber of a gas turbine;
- FIG. 3
- schematically shows a part of a tube combustion chamber in a partially perspective and partially sectioned view;
- FIG. 4
- shows a section of the already in the
FIG. 3 partially shown combustion chamber in perspective and sectional view; - FIG. 5
- schematically shows the liner area with an injector according to the invention in a perspective view;
- FIG. 6
- schematically shows a section through a portion of an injector according to the invention in a partially perspective view perpendicular to the longitudinal axis of the injector;
- FIG. 7
- schematically shows a section through a portion of an injector according to the invention in part perspective view parallel to the longitudinal axis of the injector;
- FIG. 8
- schematically shows a portion of an alternative embodiment of an injector according to the invention;
- FIG. 9
- schematically shows a section through a portion of an injector according to the invention perpendicular to the longitudinal axis of the injector.
Die
Entlang des Rotors 103 folgen aufeinander ein Ansauggehäuse 104, ein Verdichter 105, eine beispielsweise torusartige Brennkammer 110, insbesondere Ringbrennkammer, mit mehreren koaxial angeordneten Brennern 107, eine Turbine 108 und das Abgasgehäuse 109.Along the
Die Brennkammer 110 kommuniziert mit einem beispielsweise ringförmigen Heißgaskanal 111. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 112 die Turbine 108.The
Jede Turbinenstufe 112 ist beispielsweise aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 113 gesehen, folgt im Heißgaskanal 111 einer Leitschaufelreihe 115 eine aus Laufschaufeln 120 gebildete Reihe 125.Each
Die Leitschaufeln 130 sind dabei an einem Innengehäuse 138 eines Stators 143 befestigt, wohingegen die Laufschaufeln 120 einer Reihe 125 beispielsweise mittels einer Turbinenscheibe 133 am Rotor 103 angebracht sind.The guide vanes 130 are fastened to an
An dem Rotor 103 angekoppelt ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt).Coupled to the
Während des Betriebes der Gasturbine 100 wird vom Verdichter 105 durch das Ansauggehäuse 104 Luft 135 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 105 bereitgestellte verdichtete Luft wird zu den Brennern 107 geführt und dort mit einem Brennmittel vermischt. Das Gemisch wird dann unter Bildung des Arbeitsmediums 113 in der Brennkammer 110 verbrannt. Von dort aus strömt das Arbeitsmedium 113 entlang des Heißgaskanals 111 vorbei an den Leitschaufeln 130 und den Laufschaufeln 120. An den Laufschaufeln 120 entspannt sich das Arbeitsmedium 113 impulsübertragend, so dass die Laufschaufeln 120 den Rotor 103 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the
Die dem heißen Arbeitsmedium 113 ausgesetzten Bauteile unterliegen während des Betriebes der Gasturbine 100 thermischen Belastungen. Die Leitschaufeln 130 und Laufschaufeln 120 der in Strömungsrichtung des Arbeitsmediums 113 gesehen ersten Turbinenstufe 112 werden neben den die Ringbrennkammer 110 auskleidenden Hitzeschildelementen am meisten thermisch belastet.The components exposed to the hot working
Um den dort herrschenden Temperaturen standzuhalten, können diese mittels eines Kühlmittels gekühlt werden.To withstand the prevailing temperatures, they can be cooled by means of a coolant.
Als Material für die Bauteile, insbesondere für die Turbinenschaufeln 120, 130 und Bauteile der Brennkammer 110 werden beispielsweise eisen-, nickel- oder kobaltbasierte Superlegierungen verwendet.As the material for the components, in particular for the
Die Leitschaufel 130 weist einen dem Innengehäuse 138 der Turbine 108 zugewandten Leitschaufelfuß (hier nicht dargestellt) und einen dem Leitschaufelfuß gegenüberliegenden Leitschaufelkopf auf. Der Leitschaufelkopf ist dem Rotor 103 zugewandt und an einem Befestigungsring 140 des Stators 143 festgelegt.The
Die
Zur Erzielung eines vergleichsweise hohen Wirkungsgrades ist die Brennkammer 110 für eine vergleichsweise hohe Temperatur des Arbeitsmediums M von etwa 1000°C bis 1600°C ausgelegt. Um auch bei diesen, für die Materialien ungünstigen Betriebsparametern eine vergleichsweise lange Betriebsdauer zu ermöglichen, ist die Brennkammerwand 153 auf ihrer dem Arbeitsmedium M zugewandten Seite mit einer aus Hitzeschildelementen 155 gebildeten Innenauskleidung versehen.To achieve a comparatively high efficiency, the
Die
Die Brennkammer umfasst weiterhin eine Primärzone 4, in der der vom Brenner in die Brennkammer eingebrachte Brennstoff verbrannt wird. An die Primärzone schließt sich in Strömungsrichtung 3 eine Sekundärzone 5 an. In der Sekundärzone 5 wird das Heißgas aus der Primärzone 4 weiter abgebrannt. Dies erfolgt durch zusätzliches Einbringen eines Brennstoff-Luft-Gemisches 14 in die Sekundärzone 5 mit Hilfe von Injektoren 8.The combustion chamber further comprises a
Die Injektoren 8 umfassen eine Luftzufuhr 13 und einen in die Brennkammer mündenden Ausgang 9. Weiterhin ist im Inneren jedes Injektors 8 eine Brennstoffdüse 10 angeordnet. Die Brennstoffdüse 10 ist mit einem Brennstoffverteiler 11, vorzugsweise einem ringförmigen, Brennstoffverteiler 11, verbunden. Mit Hilfe der Brennstoffdüse 10 wird Brennstoff in das Innere des Injektors 8 eingedüst und auf diese Weise im Inneren des Injektors 8 ein Brennstoff-Luft-Gemisch erzeugt. Das so erzeugte Brennstoff-Luft-Gemisch wird dann durch den Injektorausgang bzw. die Eindüsöffnung 9 in die Brennkammer im Bereich der Sekundärzone 5 eingedüst.The
In der
Die
Die
Der Spiralinjektor 28 umfasst Austrittsöffnungen 9, durch die das innerhalb des Spiralinjektors 28 erzeugte Brennstoff-Luft-Gemisch in das Innere der Brennkammer eingeleitet wird. In dem in der
Der Spiralinjektor 28 umfasst einen ringförmigen Brennstoffverteiler 41, der um die äußere Oberfläche 32 des Liner-Bereichs 7 herum angeordnet ist. Der ringförmige Brennstoffverteiler 41 bildet in der hier gezeigten Ausführungsvariante zugleich den in Bezug auf die Längsachse oder Mittelachse 44 des Liner-Bereichs 7 den radial außen angeordneten Bereich des Spiralinjektors 28. Die Mittelachse oder Längsachse 44 des Liner-Bereichs 7 entspricht dabei der Mittelachse oder Längsachse des erfindungsgemäßen Injektors 28.The spiral injector 28 includes an
Der ringförmige Brennstoffverteiler 41 umfasst mindestens eine Brennstoffzufuhr 45. In der
Der Spiralinjektor 28 umfasst weiterhin zwischen dem Brennstoffverteiler 41 und der äußeren Oberfläche 32 angeordnete Strömungskanäle oder Injektorkanäle 48 (siehe dazu
Die Luftbohrungen 42 sind vorzugsweise auf beiden Seiten des Spiralinjektors, also an der stromaufwärts und der stromabwärts gelegenen Oberfläche 50 in Bezug auf die Hauptströmungsrichtung 3 vorgesehen. Die Luftbohrungen 42 sind in einzelnen Reihen nebeneinander angeordnet. Jede Luftbohrungsreihe ist einem Injektorkanal 48 zugeordnet. Der jeweilige Injektorkanal 48 und entsprechend die jeweilige Luftbohrungsreihe hat eine gebogene, vorzugsweise spiralförmig zur Mittelachse 44 hin führende Form.The air holes 42 are preferably provided on both sides of the spiral injector, that is, on the upstream and
Die Lufteinlassöffnungen oder Luftbohrungen 42 weisen jeweils eine Mittelachse 54 auf, die parallel zur Längsachse 44 des Injektors verläuft.The air inlet openings or air bores 42 each have a
In den
Der durch den ringförmigen Brennstoffverteiler 41 zu den Injektorkanälen 48 geleitete Brennstoff wird in Strömungsrichtung 46 in die Injektorkanäle 48 eingeführt. Über die Luftbohrungen 42 wird den Injektorkanälen 48 gleichzeitig Luft zugeführt. Dadurch wird im Inneren der Injektorkanäle 48 ein Brennstoff-Luft-Gemisch erzeugt, welches anschließend durch die Austrittsöffnungen 9 in die Brennkammer eingeleitet wird. Die einzelnen Injektorkanäle 48 sind durch Seitenwände 49 voneinander abgegrenzt.The fuel conducted through the
Der Spiralinjektor 28 ist senkrecht zum Liner-Bereich 7, also senkrecht zur Mittelachse 44 des Liner-Bereichs 7, installiert, wobei die Längsachse 44 des Injektors, die auch mit Mittelachse 44 des Injektors bezeichnet werden kann, bei dem dargestellten Ausführungsbeispiel mit der Mittelachse des Liners zusammenfällt. Der ringförmige Brennstoffverteiler 41 wird beispielsweise über zwei parallel angeordnete Scheiben mit dem Liner-Bereich 7 fest verbunden. In diesen Scheiben sind die Luftbohrungen 42 spiralförmig oder bogenförmig in mehreren Reihen angeordnet. Mehrere Seitenwände 49 zwischen den beiden Scheiben trennen unterschiedliche Mischkanäle bzw. Injektorkanäle 48 voneinander. Der Brennstoff wird über mehrere Öffnungen, beispielsweise Bohrungen 43, auf der Innenseite des Brennstoffverteilers 41 in die Mischkanäle 48 eingedüst. Die Luft wird senkrecht durch die spiralförmig angeordneten Luftbohrungen 42 zu der Brennstoffströmung 46 hinzugegeben und vermischt. Das Brennstoff-Luft-Gemisch gelangt anschließend in den Brennraum durch mehrere Öffnungen 9, beispielsweise Bohrungen, im Liner-Bereich 7 und entzündet sich dort.The spiral injector 28 is perpendicular to the
Die Brennstoffeinlassöffnungen 43 weisen jeweils eine Mittelachse 55 auf, die senkrecht, insbesondere tangential, zur Mittelachse 44 des Injektors verläuft.The
Die
Die
Claims (16)
- Injector (8) for introducing a fuel-air mixture into a combustion chamber, wherein
the injector (8) comprises a longitudinal axis (44) and a number of curved flow passages (48), wherein each flow passage (48) comprises a fuel inlet opening (43), a number of air inlet openings (42) and a fuel-air mixture outlet opening (9), wherein the fuel inlet opening (43) is connected to a fuel distributor (41) and the fuel-air mixture outlet opening (9) has a central axis which runs perpendicular to the longitudinal axis (44) of the injector (8), the air inlet openings (42) have in each case a central axis (54) which runs parallel to the longitudinal axis (44) of the injector (8). - Injector (8) according to Claim 1, wherein
the air inlet openings (42) of a flow passage are arranged in at least one row. - Injector (8) according to one of Claims 1 and 2, wherein
the fuel distributor (41) is of annular design. - Injector (8) according to Claim 3, wherein
the fuel distributor (41) is arranged, with respect to the longitudinal axis (44) of the injector (8), radially outside the curved flow passages (48) or is arranged, in the axial direction, next to the arcuate flow passages (48). - Injector (8) according to one of Claims 1 to 4, wherein
the curved flow passages (48) have an angle of curvature that is greater than 0° and less than 180°. - Injector (8) according to one of Claims 1 to 5, wherein
at least one of the curved flow passages (48) has an axis of curvature which runs parallel to the longitudinal axis (44) of the injector (8). - Injector (8) according to one of Claims 1 to 6, wherein
the injector (8) comprises two disks which are arranged substantially parallel to one another, wherein the disks comprise the sidewalls (49) of the flow passages (48) and the air inlet openings (42). - Combustion chamber which comprises at least one injector (8) according to one of Claims 1 to 7.
- Combustion chamber according to Claim 8 when the combustion chamber comprises at least one injector (8) only according to Claim 1, wherein
the injector (8) is arranged on the combustion chamber such that its longitudinal axis (44) runs substantially parallel to a longitudinal axis (102) of the combustion chamber or coincides therewith. - Combustion chamber according to Claim 8, wherein
the combustion chamber comprises a longitudinal axis (102), a combustion chamber head end, a combustion chamber outlet (6), a combustion chamber wall (1) which extends from the combustion chamber head end to the combustion chamber outlet (6), a primary zone (4) and a secondary zone (5), which is arranged downstream of the primary zone (4) in the main flow direction (3) of the hot gas, and the at least one injector (8) is arranged on the combustion chamber wall (1) such that the fuel-air mixture outlet openings (9) open into the secondary zone. - Combustion chamber according to Claim 8 or Claim 10, wherein
the fuel-air mixture outlet openings (9) are arranged along a circumferential line on the combustion chamber wall (1). - Combustion chamber according to one of Claims 8, 10 and 11, wherein
the combustion chamber comprises a liner region (7) which comprises the at least one injector (8). - Combustion chamber according to Claim 12, wherein
the liner region (7) comprises a longitudinal axis (44) which coincides with the longitudinal axis of the injector (8). - Combustion chamber according to Claim 12 or Claim 13, wherein
the liner region (7) is designed as a separate component. - Combustion chamber according to one of Claims 8, 10 to 14, wherein
the combustion chamber is designed as an annular combustion chamber (106) or as a tubular combustion chamber. - Gas turbine (100) which comprises a combustion chamber according to one of Claims 8 to 15.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13170048.6A EP2808611B1 (en) | 2013-05-31 | 2013-05-31 | Injector for introducing a fuel-air mixture into a combustion chamber |
US14/289,184 US20140352312A1 (en) | 2013-05-31 | 2014-05-28 | Injector for introducing a fuel-air mixture into a combustion chamber |
CN201410235334.7A CN104213986A (en) | 2013-05-31 | 2014-05-29 | Injector for introducing a fuel-air mixture into a combustion chamber |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13170048.6A EP2808611B1 (en) | 2013-05-31 | 2013-05-31 | Injector for introducing a fuel-air mixture into a combustion chamber |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2808611A1 EP2808611A1 (en) | 2014-12-03 |
EP2808611B1 true EP2808611B1 (en) | 2015-12-02 |
Family
ID=48577533
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13170048.6A Not-in-force EP2808611B1 (en) | 2013-05-31 | 2013-05-31 | Injector for introducing a fuel-air mixture into a combustion chamber |
Country Status (3)
Country | Link |
---|---|
US (1) | US20140352312A1 (en) |
EP (1) | EP2808611B1 (en) |
CN (1) | CN104213986A (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150159877A1 (en) * | 2013-12-06 | 2015-06-11 | General Electric Company | Late lean injection manifold mixing system |
US9803555B2 (en) * | 2014-04-23 | 2017-10-31 | General Electric Company | Fuel delivery system with moveably attached fuel tube |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US12066188B2 (en) * | 2021-03-26 | 2024-08-20 | Rtx Corporation | Modular injector bolt for an engine |
US12072101B2 (en) | 2022-02-18 | 2024-08-27 | Rtx Corporation | Fuel injector with splash plate for an engine |
CN115234943A (en) * | 2022-06-30 | 2022-10-25 | 北京航空航天大学 | Center grading and axial grading coupling type combustion chamber |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
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US2417445A (en) * | 1945-09-20 | 1947-03-18 | Pinkel Benjamin | Combustion chamber |
US4420929A (en) * | 1979-01-12 | 1983-12-20 | General Electric Company | Dual stage-dual mode low emission gas turbine combustion system |
US4928481A (en) * | 1988-07-13 | 1990-05-29 | Prutech Ii | Staged low NOx premix gas turbine combustor |
DE4232383A1 (en) | 1992-09-26 | 1994-03-31 | Asea Brown Boveri | Gas turbine group |
JP2950720B2 (en) | 1994-02-24 | 1999-09-20 | 株式会社東芝 | Gas turbine combustion device and combustion control method therefor |
GB9410233D0 (en) * | 1994-05-21 | 1994-07-06 | Rolls Royce Plc | A gas turbine engine combustion chamber |
GB2307980B (en) * | 1995-12-06 | 2000-07-05 | Europ Gas Turbines Ltd | A fuel injector arrangement; a method of operating a fuel injector arrangement |
US6047550A (en) | 1996-05-02 | 2000-04-11 | General Electric Co. | Premixing dry low NOx emissions combustor with lean direct injection of gas fuel |
DE69916911T2 (en) * | 1998-02-10 | 2005-04-21 | Gen Electric | Burner with uniform fuel / air premix for low-emission combustion |
US6735949B1 (en) * | 2002-06-11 | 2004-05-18 | General Electric Company | Gas turbine engine combustor can with trapped vortex cavity |
US6868676B1 (en) | 2002-12-20 | 2005-03-22 | General Electric Company | Turbine containing system and an injector therefor |
US20070107437A1 (en) | 2005-11-15 | 2007-05-17 | Evulet Andrei T | Low emission combustion and method of operation |
FR2920523B1 (en) * | 2007-09-05 | 2009-12-18 | Snecma | TURBOMACHINE COMBUSTION CHAMBER WITH AIR HELICOIDAL CIRCULATION. |
US8387398B2 (en) | 2007-09-14 | 2013-03-05 | Siemens Energy, Inc. | Apparatus and method for controlling the secondary injection of fuel |
US20090249789A1 (en) * | 2008-04-08 | 2009-10-08 | Baifang Zuo | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
EP2246617B1 (en) * | 2009-04-29 | 2017-04-19 | Siemens Aktiengesellschaft | A burner for a gas turbine engine |
US8991192B2 (en) | 2009-09-24 | 2015-03-31 | Siemens Energy, Inc. | Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine |
US8683804B2 (en) * | 2009-11-13 | 2014-04-01 | General Electric Company | Premixing apparatus for fuel injection in a turbine engine |
US8590311B2 (en) * | 2010-04-28 | 2013-11-26 | General Electric Company | Pocketed air and fuel mixing tube |
CH707282B1 (en) * | 2011-09-22 | 2015-12-15 | Gen Electric | Burner and method for supplying fuel to a burner. |
-
2013
- 2013-05-31 EP EP13170048.6A patent/EP2808611B1/en not_active Not-in-force
-
2014
- 2014-05-28 US US14/289,184 patent/US20140352312A1/en not_active Abandoned
- 2014-05-29 CN CN201410235334.7A patent/CN104213986A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
CN104213986A (en) | 2014-12-17 |
EP2808611A1 (en) | 2014-12-03 |
US20140352312A1 (en) | 2014-12-04 |
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