EP0320746B1 - Gas turbine plant - Google Patents

Gas turbine plant Download PDF

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Publication number
EP0320746B1
EP0320746B1 EP88120316A EP88120316A EP0320746B1 EP 0320746 B1 EP0320746 B1 EP 0320746B1 EP 88120316 A EP88120316 A EP 88120316A EP 88120316 A EP88120316 A EP 88120316A EP 0320746 B1 EP0320746 B1 EP 0320746B1
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EP
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Prior art keywords
combustion chamber
gas turbine
stage
turbine plant
plant according
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EP88120316A
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German (de)
French (fr)
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EP0320746A1 (en
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Günter. Prof. Dr.-Ing. Kappler
Dieter Dr. Ing. Rist
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Bayerische Motoren Werke AG
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Bayerische Motoren Werke AG
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Definitions

  • the invention relates to a gas turbine system of the type specified in the preamble of the first claim and to a method for operating such a gas turbine system according to the preamble of claim 18.
  • the influencing factors to be taken into account in the design which are decisive for the formation of pollutants, result from the analysis of the reaction kinetic processes in the combustion chamber.
  • the most important influencing factors here are the primary zone temperature and the equivalence ratio, the degree of premixing and the combustion homogeneity in the primary zone, the residence time of the combustion products in the primary zone, the "freezing" of the reaction products near the wall of the combustion chamber and the intermediate zone temperature and residence time.
  • the object of the present invention is to propose a space-saving structure for a gas turbine system with compressor and turbine impellers of the type mentioned at the outset.
  • this object is achieved by the characterizing features of the first claim.
  • the advantage of this solution is that compact dimensions of the entire system can be achieved, since all supply lines for the second stage of the combustion chamber in the Annulus can be placed.
  • the combustion air for the second stage has a cooling effect for this. This has become possible because the center of the combustion chamber forms a self-contained interior, which is connected to the combustion chambers only via the air supply openings. This will surely prevent flames from entering.
  • the flow restriction between the first and second stage - as the development according to claim 2 describes - has the advantage that flame flashbacks from the second stage of the combustion chamber are avoided.
  • the pre-evaporator (s) must be designed so that they cause a slight pressure loss and ensure a sufficient residence time for the fuel to evaporate almost completely.
  • the development according to claim 4 has the advantage that the already vaporized fuel is homogeneously mixed with the air. This prevents non-uniform mixing, so that no local fuel enrichment, which leads to the formation of flashbacks in the lean fuel-air mixture when stoichiometric conditions are reached, cannot take place.
  • the design of the mixing zone according to the principle of the diffusion burner also has the advantage that the mixing times are limited below the ignition delay times.
  • a preferred arrangement of the catalytic converter is described in claim 6.
  • the first are due to the progressive increase in temperature during fuel oxidation Catalyst segments constructed so that they become active at low reaction temperatures.
  • the subsequent catalyst segments have a high oxidation effect, so that the reaction temperature and thus the air heating increases.
  • catalyst segments are created that are economically producible. They are characterized by a support structure consisting of a substrate and an intermediate adhesive layer, onto which the catalyst is evaporated. Claims 8 and 9 describe suitable materials.
  • the porosity of the substrate is chosen so that the pressure loss is small. With the development according to claim 10, a pressure loss is achieved in the entire combustion chamber, which is not greater than 5%.
  • the combustion chamber is designed as an annular combustion chamber, the space lying in the longitudinal axis can be used for additional components - as taught in claim 12.
  • the air creates cooling and thermal insulation from the hot walls of the combustion chamber.
  • the fuel lines to the second stage of the combustion chamber can also be arranged there without additional heat insulation measures having to be provided, without which the fuel would evaporate in its lines, so that deposits could form which would lead to the lines becoming overgrown.
  • Claims 13 and 14 describe two alternative possibilities for controlling the air inlet openings.
  • a simplification - without negatively influencing the combustion in the second stage of the combustion chamber - describes the control of the air inlet opening.
  • Claims 18-20 describe a preferred method for operating the gas turbine system with the combustion chamber constructed according to the invention. For example, due to the design of the two-stage combustion chamber, combustion can be initiated to start it and the catalyst can be warmed up from the rear, as it were. This happens very quickly, so that the fuel oxidation can be initiated in the first stage of the combustion chamber shortly after the start.
  • the development according to claim 19 ensures that the temperature increase in the combustion chamber can be controlled in order to achieve optimum burnout levels.
  • the second stage of the combustion chamber is also suitable for achieving acceleration values of the gas turbine similar to the reciprocating piston engine and for covering power peaks.
  • a two-shaft gas turbine system is shown schematically as an example. It consists in a manner known per se from the compressor 1, the heat exchanger 2, the combustion chamber 3, the compressor turbine 4 and the power turbine 5.
  • a reduction gear 6 known per se is arranged on the output shaft of the power turbine 5, the output shaft of which - when using the Gas turbine system in a motor vehicle - is connected to the motor vehicle transmission.
  • the compressor 1 draws in ambient air and guides it through the heat exchanger 2, through which the heated exhaust gases flow after leaving the power turbine 5.
  • the compressed and heated air is passed into the combustion chamber 3, where it undergoes a further temperature increase with the aid of fuel. It is then passed to the compressor turbine 4 for driving the compressor 1 and to the utility turbine 5 for driving the reduction gear 6, from where it is discharged into the environment after flowing through the heat exchanger 2 and possibly silencing devices.
  • combustion chamber shown in FIG. 2 is provided.
  • the second shows a side view in the upper half of the figure and a schematic cross section through the combustion chamber 3 constructed according to the invention in the lower half of the figure.
  • This is constructed as a two-stage head-ring combustion chamber with a longitudinal axis 7 and the two stages 8 and 9.
  • the first stage 8 is designed as a main combustion chamber.
  • the fuel is introduced via pre-evaporators 10, which are arranged in a star shape on the outer end face 11.
  • the air necessary for fuel oxidation, compressed by the compressor 1 and heated via the heat exchanger 2 flows into the combustion chamber via air inlet openings 12, which are arranged on the diffuser-like circumference of the first stage 8.
  • air and vaporized fuel mix to form a homogeneous mixture, the mixing times remaining below the ignition delay times due to the design of the main combustion chamber.
  • the vaporous fuel-air mixture then arrives at the catalyst 14, which is constructed from individual annular segments 15 arranged coaxially to the longitudinal axis 7. This leads to a tiered catalysis.
  • segments 15 are used which are active at low reaction temperatures. They are followed by further segments 15 of high oxidation effectiveness, in which the reaction temperature and thus the air heating increases.
  • These catalytic segments are fastened in supporting structures and consist of a substrate and an intermediate adhesive layer, onto which the catalyst material from the platinum material group is evaporated. Due to the high operating temperatures of approx. 1450 ° K, high demands are placed on the materials.
  • the porosity of the substrate using magnesium, aluminum and titanium alloys is set so that the pressure drop is small. A pressure loss of the entire combustion chamber of no more than 5% can be achieved if the substrate structure has at least 50 cells / cm2.
  • the reaction products flow from the catalyst 14 through the flow restriction 16 into the second stage 9 of the combustion chamber 3.
  • the flow restriction 16 has the task of preventing flashbacks from the second stage of the combustion chamber into the catalyst, which would lead to its inevitable destruction.
  • the fuel is introduced into the second stage 9 of the combustion chamber 3 with the aid of air-assisted atomizing nozzles 17.
  • the spark plugs 18 are provided for igniting the fuel-air mixture located in the second stage 9.
  • the atomizer nozzles 17 are arranged on the inner wall of the combustion chamber and are supplied with fuel via fuel supply lines 19 located within the annular combustion chamber. These branch off from the main fuel line 20 to which the pre-evaporators 10 are connected.
  • the second stage 9 of the combustion chamber 3 has air inlet openings 21 and 22 distributed over its circumference, the air inlet openings 21 being arranged on the outside and the air inlet openings 22 being arranged on the inside of the annular head combustion chamber.
  • the inner air inlet openings 22 are provided with a perforated ring 23 which can be rotated by an actuator 24 via actuators 25. Both the servomotor 24 and the actuators 25 can be arranged coaxially to the longitudinal axis 7 of the combustion chamber will. Separate heat insulation means are not necessary here if the interior enclosed by the annular combustion chamber is cooled due to the air supplied.
  • the air supply via the perforated ring 23 and the fuel supply via the atomizing nozzles 17 are increased again in the second stage of the combustion chamber 3, so that a noticeable afterburning takes place and thus a noticeable increase in temperature. This is also done at full load.

Description

Die Erfindung bezieht sich auf eine Gasturbinenanlage der im Oberbegriff des ersten Anspruchs angegebenen Art sowie auf ein Verfahren zum Betreiben einer solchen Gasturbinenanlage nach dem Oberbegriff des Anspruchs 18.The invention relates to a gas turbine system of the type specified in the preamble of the first claim and to a method for operating such a gas turbine system according to the preamble of claim 18.

Bei der bisherigen Auslegung von Brennkammern für Gasturbinen, die in Kraftfahrzeugen, insbesondere in Personenkraftwagen eingesetzt werden sollen, hat man bisher nur Wert darauf gelegt, einen hohen Ausbrenngrad und eine gleichmäßige Temperaturverteilung zu erzielen.In the previous design of combustion chambers for gas turbines, which are to be used in motor vehicles, in particular in passenger cars, until now it has only been important to achieve a high degree of burnout and a uniform temperature distribution.

Aufgrund gesetzlicher Verschärfungen auf dem Abgassektor von Brennkraftmaschinen müssen nun auch bei der Konstruktion von Gasturbinen und hier insbesondere deren Brennkammern auf die festgelegten Schadstoffemissionsgrenzen erhöhter Wert gelegt werden. Die bei der Auslegung zu berücksichtigenden Einflußgrößen, die für die Schadstoffentstehung bestimmend sind, ergeben sich aus der Analyse der reaktionskinetischen Vorgänge in der Brennkammer. Die wichtigsten Einflußgrößen hierbei sind die Primärzonentemperatur und das Äquivalenzverhältnis, der Grad der Vorvermischung und der Verbrennungshomogenität in der Primärzone, die Verweilzeit der Verbrennungsprodukte in der Primärzone, das "Einfrieren" der Reaktionsprodukte in Wandnähe der Brennkammer und die Zwischenzonentemperatur und -verweilzeit.Due to legal tightening in the exhaust gas sector of internal combustion engines, increased value must now also be placed on the specified pollutant emission limits when designing gas turbines and in particular their combustion chambers. The influencing factors to be taken into account in the design, which are decisive for the formation of pollutants, result from the analysis of the reaction kinetic processes in the combustion chamber. The most important influencing factors here are the primary zone temperature and the equivalence ratio, the degree of premixing and the combustion homogeneity in the primary zone, the residence time of the combustion products in the primary zone, the "freezing" of the reaction products near the wall of the combustion chamber and the intermediate zone temperature and residence time.

Die Schwierigkeiten der Auslegung schadstoffarmer Brennkammern besteht in der gegensätzlichen Auswirkung der Einflußgrößen auf die einzelnen Schadstoffanteile. So führen z.B. niedrige Primärzonentemperaturen zu einer geringen NO-Emission, jedoch gleichzeitig zu einer hohen CO-Konzentration aufgrund der verminderten Oxidationsrate.The difficulty in designing low-emission combustion chambers is the opposite effect of the influencing variables on the individual pollutant components. For example, low primary zone temperatures lead to low NO emissions, but at the same time to a high CO concentration due to the reduced oxidation rate.

Um dieses Problem zu lösen, ist es aus der EP-A-0144094 bekannt, eine katalytisch unterstützte Verbrennung vorzusehen, indem ein Katalysator in der als Kopfbrennkammer ausgebildeten ersten Stufe der Zweistufenbrennkammer vorgesehen wurde. Aufgrund der katalytisch unterstützten Verbrennung kann die Brennstoffoxidation über die Erlöschgrenze hinaus zu sehr mageren Brennstoff-Luft-Verhältnissen und zu niedrigen Reaktionstemperaturen verlagert werden. Somit besteht eine Möglichkeit, gleichzeitig die NO- und CO-Emission zu vermindern, ohne die Leistungsausbeutung zu senken oder den Brennstoffverbrauch zu erhöhen. Als Brennstoffe können in der Brennkammer flüssige oder gasförmige Kohlenwasserstoffe, Kohlesuspension und Wasserstoff eingesetzt werden.In order to solve this problem, it is known from EP-A-0144094 to provide catalytically assisted combustion by providing a catalyst in the first stage of the two-stage combustion chamber designed as a top combustion chamber. Due to the catalytically assisted combustion, the fuel oxidation can be shifted beyond the extinction limit to very lean fuel-air ratios and to low reaction temperatures. There is thus a possibility of simultaneously reducing the NO and CO emissions without reducing the performance exploitation or increasing the fuel consumption. Liquid or gaseous hydrocarbons, coal suspension and hydrogen can be used as fuels in the combustion chamber.

Aufgabe der vorliegenden Erfindung ist es, für eine Gasturbinenanlage mit Verdichter- und Turbinenlaufräder der eingangs genannten Art einen platzsparenden Aufbau vorzuschlagen.The object of the present invention is to propose a space-saving structure for a gas turbine system with compressor and turbine impellers of the type mentioned at the outset.

Diese Aufgabe wird erfindungsgemäß durch die kennzeichnenden Merkmale des ersten Anspruchs gelöst. Der Vorteil dieser Lösung besteht darin, daß kompakte Abmessungen der gesamten Anlage erzielt werden, da sämtliche Versorgungsleitungen für die zweite Stufe der Brennkammer in den Ringraum gelegt werden können. Die Verbrennungsluft für die zweite Stufe übt hierfür eine Kühlwirkung aus. Dies ist möglich geworden, da das Zentrum der Brennkammer einen in sich abgeschlossenen Innenraum bildet, der mit den Brennkammern nur über die Luftzuführungsöffnungen in Verbindung steht. Dadurch wird sicher vermieden, daß dort Flammen eintreten können.According to the invention, this object is achieved by the characterizing features of the first claim. The advantage of this solution is that compact dimensions of the entire system can be achieved, since all supply lines for the second stage of the combustion chamber in the Annulus can be placed. The combustion air for the second stage has a cooling effect for this. This has become possible because the center of the combustion chamber forms a self-contained interior, which is connected to the combustion chambers only via the air supply openings. This will surely prevent flames from entering.

Aus der US-A-4,047,877 ist es bekannt, in Brennkammern kreisringförmige Katalysatoren zu verwenden. Diese Brennkammern können zwar auch als Energiequelle in einem Turbinensystem angewendet werden, wie eingangs in dieser Patentschrift ausgeführt ist. Diese Eignung ist jedoch bei den hier interessierenden Ausführungsbeispielen nach den Fig. 9 bis 12 ausgeschlossen, da nicht erkennbar ist, wie die notwendige Anordnung von Verdichter- und Turbinenrad samt Lagerung bewerkstelligt werden soll, da das Zentrum nicht frei von Flammen gehalten werden kann. Deshalb werden auch die Versorgungsleitungen für die zweite Stufe der Brennkammer von außen radial zugeführt.From US-A-4,047,877 it is known to use annular catalysts in combustion chambers. These combustion chambers can also be used as an energy source in a turbine system, as stated at the beginning of this patent. However, this suitability is excluded in the exemplary embodiments according to FIGS. 9 to 12, which are of interest here, since it cannot be seen how the necessary arrangement of the compressor and turbine wheel including the bearing is to be accomplished, since the center cannot be kept free from flames. Therefore, the supply lines for the second stage of the combustion chamber are supplied radially from the outside.

Im Gegensatz hierzu wird jedoch gemäß der Erfindung die Anordnung der Versorgungsleitung außerhalb der Brennkammer vermieden und eine kompakte Anordnung der Gasturbinenanlage erzielt.In contrast to this, however, the arrangement of the supply line outside the combustion chamber is avoided and a compact arrangement of the gas turbine system is achieved according to the invention.

Die Strömungsverengung zwischen der ersten und zweiten Stufe ― wie die Weiterbildung nach Anspruch 2 beschreibt ― hat den Vorteil, daß hierdurch Flammenrückschläge aus der zweiten Stufe der Brennkammer vermieden werden.The flow restriction between the first and second stage - as the development according to claim 2 describes - has the advantage that flame flashbacks from the second stage of the combustion chamber are avoided.

Eine bevorzugte Einbringungsmöglichkeit des Brennstoffs in die erste Stufe der Brennkammer, die eine gute und schnelle Vermischung mit der Luft sicherstellt, beschreibt Anspruch 3. Hierbei ist bzw. sind der bzw. die Vorverdampfer so auszulegen, daß er bzw. sie einen geringen Druckverlust bewirken und eine ausreichende Aufenthaltszeit zur nahezu vollständigen Verdampfung des Brennstoffs gewährleisten.A preferred possibility of introducing the fuel into the first stage of the combustion chamber, which ensures good and rapid mixing with the air, is described in claim 3. Here, the pre-evaporator (s) must be designed so that they cause a slight pressure loss and ensure a sufficient residence time for the fuel to evaporate almost completely.

Die Weiterbildung nach Anspruch 4 hat den Vorteil, daß dadurch der bereits verdampfte Brennstoff homogen mit der Luft gemischt wird. Dadurch wird eine ungleichförmige Vermischung verhindert, so daß keine lokalen Brennstoffanreicherungen, die bei Erreichen stöchiometrischer Verhältnisse zur Ausbildung von Flammenrückschlägen in das insgesamt magere Brennstoff-Luft-Gemischführen, stattfinden können. Die Auslegung der Vermischungszone nach dem Prinzip des Diffusionsbrenners hat darüber hinaus den Vorteil, daß die Mischungszeiten unterhalb der Zündverzugszeiten begrenzt werden.The development according to claim 4 has the advantage that the already vaporized fuel is homogeneously mixed with the air. This prevents non-uniform mixing, so that no local fuel enrichment, which leads to the formation of flashbacks in the lean fuel-air mixture when stoichiometric conditions are reached, cannot take place. The design of the mixing zone according to the principle of the diffusion burner also has the advantage that the mixing times are limited below the ignition delay times.

Durch die Weiterbildung nach Anspruch 5 ist es möglich, einen einfach aufgebauten und zu fertigenden Katalysator zu schaffen, der den Erfordernissen nach einer vollständigen Verbrennung bei gleichzeitiger Verminderung der NO- und CO-Emission durch einen einfachen Aufbau gewährleistet.Through the development according to claim 5, it is possible to create a catalyst of simple construction and to be manufactured, which ensures the requirements for complete combustion with a simultaneous reduction in NO and CO emissions through a simple structure.

Eine bevorzugte Anordnung des Katalysators beschreibt Anspruch 6. Aufgrund der fortschreitenden Temperaturerhöhung bei der Brennstoffoxidation sind die ersten Katalysatorsegmente so aufgebaut, daß sie bei niedrigen Reaktionstemperaturen aktiv werden. Die sich anschließenden Katalysatorsegmente weisen einen hohen Oxidationseffekt auf, so daß sich die Reaktionstemperatur und damit die Luftaufheizung erhöht.A preferred arrangement of the catalytic converter is described in claim 6. The first are due to the progressive increase in temperature during fuel oxidation Catalyst segments constructed so that they become active at low reaction temperatures. The subsequent catalyst segments have a high oxidation effect, so that the reaction temperature and thus the air heating increases.

Durch die Weiterbildung nach Anspruch 7 werden Katalysatorsegmente geschaffen, die wirtschaftlich herstellbar sind. Sie zeichnen sich durch eine Tragestruktur aus, die aus einem Substrat sowie einer Zwischenhaftschicht bestehen, auf die der Katalysator aufgedampft wird. Die Ansprüche 8 und 9 beschreiben geeignete Werkstoffe.Through the development according to claim 7, catalyst segments are created that are economically producible. They are characterized by a support structure consisting of a substrate and an intermediate adhesive layer, onto which the catalyst is evaporated. Claims 8 and 9 describe suitable materials.

Die Porösität des Substrates wird so gewählt, daß der Druckverlust klein ist. Mit der Weiterbildung nach Anspruch 10 wird ein Druckverlust in der gesamten Brennkammer erreicht, der nicht größer als 5% ist.The porosity of the substrate is chosen so that the pressure loss is small. With the development according to claim 10, a pressure loss is achieved in the entire combustion chamber, which is not greater than 5%.

Zur Steuerung der Verbrennung in der zweiten Stufe der Brennkammer wird die Weiterbildung nach Anspruch 11 vorgeschlagen. Damit wird eine gesteuerte Nachverbrennung zur Einstellung von maximalen Prozeßtemperaturen erreicht.To control the combustion in the second stage of the combustion chamber, the development according to claim 11 is proposed. A controlled afterburning for setting maximum process temperatures is thus achieved.

Da die Brennkammer als Ringbrennkammer ausgebildet ist, kann der in Längsachse liegende Raum für zusätzliche Bauteile ― wie Anspruch 12 lehrt ― genutzt werden. Hierbei wird durch die Luft eine Kühlung und Wärmeisolation gegenüber den heißen Wänden der Brennkammer geschaffen. Auch können dort die Brennstoffleitungen zur zweiten Stufe der Brennkammer angeordnet werden, ohne daß zusätzliche Wärmeisolationsmaßnahmen vorgesehen werden müssen, ohne die der Brennstoff in seinen Leitungen verdampfen würde, so daß sich Ablagerungen bilden könnten, die zu einem Zuwachsen der Leitungen führen würden.Since the combustion chamber is designed as an annular combustion chamber, the space lying in the longitudinal axis can be used for additional components - as taught in claim 12. The air creates cooling and thermal insulation from the hot walls of the combustion chamber. The fuel lines to the second stage of the combustion chamber can also be arranged there without additional heat insulation measures having to be provided, without which the fuel would evaporate in its lines, so that deposits could form which would lead to the lines becoming overgrown.

Aufgrund der vorgeschlagenen Brennkammergeometrie ist hierbei auch eine ausreichende Lagerungsmöglichkeit für den Stellmotor und die Betätigungsglieder gegeben, so daß eine exakte Steuerung der Lufteinlaßöffnungen bei hoher Lebensdauer der Betätigungsglieder und des Stellmotors erzielt wird.Due to the proposed combustion chamber geometry, there is also sufficient storage for the actuator and the actuators, so that precise control of the air inlet openings is achieved with a long service life of the actuators and the actuator.

Zwei alternative Möglichkeiten zur Steuerung der Lufteinlaßöffnungen beschreiben Anspruch 13 und 14. Eine Vereinfachung ― ohne negative Beeinflußung der Verbrennung in der zweiten Stufe der Brennkammer ― der Steuerung der Lufteintrittsöffnung beschreibt Anspruch 15.Claims 13 and 14 describe two alternative possibilities for controlling the air inlet openings. A simplification - without negatively influencing the combustion in the second stage of the combustion chamber - describes the control of the air inlet opening.

Um eine gute Zerstäubung zu erreichen, wird die Weiterbildung nach Anspruch 16 vorgeschlagen. Die Lage der notwendigen Zündeinrichtungen beschreibt Anspruch 17.In order to achieve good atomization, the training according to claim 16 is proposed. The location of the necessary ignition devices is described in claim 17.

Die Ansprüche 18-20 beschreiben ein bevorzugtes Verfahren zum Betreiben der Gasturbinenanlage mit der erfindungsgemäß aufgebauten Brennkammer. So kann aufgrund der Ausbildung der zweistufigen Brennkammer dort die Verbrennung zum Starten eingeleitet werden und so der Katalysator gleichsam von rückwärts erwärmt werden. Dies geschieht sehr schnell, so daß bereits kurze Zeit nach dem Start die Brennstoffoxidation in der ersten Stufe der Brennkammer eingeleitet werden kann.Claims 18-20 describe a preferred method for operating the gas turbine system with the combustion chamber constructed according to the invention. For example, due to the design of the two-stage combustion chamber, combustion can be initiated to start it and the catalyst can be warmed up from the rear, as it were. This happens very quickly, so that the fuel oxidation can be initiated in the first stage of the combustion chamber shortly after the start.

Durch die Weiterbildung nach Anspruch 19 wird erreicht, daß die Temperaturerhöhung in der Brennkammer gesteuert werden kann, um optimale Ausbrenngrade zu erzielen.The development according to claim 19 ensures that the temperature increase in the combustion chamber can be controlled in order to achieve optimum burnout levels.

Um Beschleunigungswerte der Gasturbine ähnlich dem Hubkolbenmotor zu erzielen, sowie um Leistungsspitzen abzudecken, eignet sich ebenfalls die zweite Stufe der Brennkammer, wie Anspruch 20 vorschlägt.The second stage of the combustion chamber is also suitable for achieving acceleration values of the gas turbine similar to the reciprocating piston engine and for covering power peaks.

Im folgenden wird die Erfindung anhand eines bevorzugten Ausführungsbeispiels näher beschrieben. Es stellen dar:

Fig. 1
einen schematisierten Aufbau einer Gasturbinenanlage für Fahrzeuge;
Fig. 2
eine Längsansicht, teilweise als Längsschnitt der erfindungsgemäß aufgebauten Brennkammer.

The invention is described in more detail below with the aid of a preferred exemplary embodiment. They represent:
Fig. 1
a schematic structure of a gas turbine system for vehicles;
Fig. 2
a longitudinal view, partially as a longitudinal section of the combustion chamber constructed according to the invention.

In Fig. 1 ist als Beispiel schematisiert einen Zweiwellen-Gasturbinenanlage dargestellt. Sie besteht in an sich bekannter Weise aus dem Verdichter 1, dem Wärmetauscher 2, der Brennkammer 3, der Verdichterturbine 4 sowie der Nutzturbine 5. An der Ausgangswelle der Nutzturbine 5 ist ein an sich bekanntes Untersetzungsgetriebe 6 angeordnet, dessen Ausgangswelle ― bei der Verwendung der Gasturbinenanlage in einem Kraftfahrzeug ― mit dem Kraftfahrzeuggetriebe verbunden ist.In Fig. 1, a two-shaft gas turbine system is shown schematically as an example. It consists in a manner known per se from the compressor 1, the heat exchanger 2, the combustion chamber 3, the compressor turbine 4 and the power turbine 5. A reduction gear 6 known per se is arranged on the output shaft of the power turbine 5, the output shaft of which - when using the Gas turbine system in a motor vehicle - is connected to the motor vehicle transmission.

Der Verdichter 1 saugt Umgebungsluft an und führt sie durch den Wärmetauscher 2, der von den erwärmten Abgasen nach Verlassen der Nutzturbine 5 durchströmt wird. Die so verdichtete und erwärmte Luft wird in die Brennkammer 3 geleitet, wo sie mit Hilfe von Brennstoff eine weitere Temperaturerhöhung erfährt. Sodann wird sie zu der Verdichterturbine 4 zum Antrieb des Verdichters 1 und zu der Nutzturbine 5 zum Antrieb des Untersetzungsgetriebes 6 geleitet, von wo aus sie nach Durchströmen des Wärmetauschers 2 und evtl. Schalldämpfeinrichtungen in die Umgebung abgeführt wird.The compressor 1 draws in ambient air and guides it through the heat exchanger 2, through which the heated exhaust gases flow after leaving the power turbine 5. The compressed and heated air is passed into the combustion chamber 3, where it undergoes a further temperature increase with the aid of fuel. It is then passed to the compressor turbine 4 for driving the compressor 1 and to the utility turbine 5 for driving the reduction gear 6, from where it is discharged into the environment after flowing through the heat exchanger 2 and possibly silencing devices.

Um eine derartige Gasturbinenanlage mit max. Prozeßtemperaturen und geringer Schadstoffemission sowie optimalen Start- und Vollast- sowie Beschleunigungsbedingungen betreiben zu können, wird die in Fig. 2 dargestellte Brennkammer vorgesehen.To such a gas turbine system with max. To be able to operate process temperatures and low pollutant emissions as well as optimal starting and full load as well as acceleration conditions, the combustion chamber shown in FIG. 2 is provided.

Fig. 2 zeigt in der oberen Bildhälfte eine Seitenansicht und in der unteren Bildhäfte einen schematisierten Querschnitt durch die erfindungsgemäß aufgebaute Brennkammer 3. Diese ist als zweistufige Kopf-Ringbrennkammer mit einer Längsachse 7 und den beiden Stufen 8 und 9 aufgebaut. Die erste Stufe 8 ist als Hauptbrennkammer ausgeführt. Der Brennstoff wird über Vorverdampfer 10, die sternförmig auf der äußeren Stirnseite 11 verteilt angeordnet sind, eingebracht. Über Lufteinlaßöffnungen 12, die auf dem diffusorartig ausgebildeten Umfang der ersten Stufe 8 angeordnet sind, strömt die zur Brennstoffoxidation notwendige, von dem Verdichter 1 verdichtete und über den Wärmetauscher 2 erhitzte Luft in die Brennkammer. In der Vorvermischungszone 13 mischen sich Luft und verdampfter Brennstoff zu einer homogenen Mischung, wobei die Mischungszeiten aufgrund der Auslegung der Hauptbrennkammer unterhalb der Zündverzugszeiten bleiben.2 shows a side view in the upper half of the figure and a schematic cross section through the combustion chamber 3 constructed according to the invention in the lower half of the figure. This is constructed as a two-stage head-ring combustion chamber with a longitudinal axis 7 and the two stages 8 and 9. The first stage 8 is designed as a main combustion chamber. The fuel is introduced via pre-evaporators 10, which are arranged in a star shape on the outer end face 11. The air necessary for fuel oxidation, compressed by the compressor 1 and heated via the heat exchanger 2, flows into the combustion chamber via air inlet openings 12, which are arranged on the diffuser-like circumference of the first stage 8. In the premixing zone 13, air and vaporized fuel mix to form a homogeneous mixture, the mixing times remaining below the ignition delay times due to the design of the main combustion chamber.

Sodann gelangt das dampfförmige Brennstoff-Luft-Gemisch zu dem Katalysator 14, welcher aus einzelnen koaxial zur Längsachse 7 angeordneten ringförmigen Segmenten 15 aufgebaut ist. Dadurch wird eine gestufte Katalyse bewirkt. Am Eintritt des Brennstoff-Luft-Gemisches werden Segmente 15 verwendet, die bei niedrigen Reaktionstemperaturen aktiv sind. Ihnen schließen sich weitere Segmente 15 hoher Oxidationseffektivität an, in denen sich die Reaktionstemperatur und damit die Luftaufheizung erhöht. Diese katalytischen Segmente sind in Tragstrukturen befestigt und bestehen aus einem Substrat sowie einer Zwischenhaftschicht, auf die der Katalysatorwerkstoff aus der Werkstoffgruppe des Platins aufgedampft ist. Aufgrund der hohen Betriebstemperaturen von ca. 1450° K werden hohe Anforderungen an die Werkstoffe gestellt. Die Porösität des Substrates, für das man Legierungen aus Magnesium, Aluminium und Titan verwendet, wird so eingestellt, daß der Druckverlust klein ist. Man kann einen Druckverlust der gesamten Brennkammer von nicht mehr als 5% erreichen, wenn die Substratstruktur mindestens 50 Zellen/cm² aufweist.The vaporous fuel-air mixture then arrives at the catalyst 14, which is constructed from individual annular segments 15 arranged coaxially to the longitudinal axis 7. This leads to a tiered catalysis. At the entry of the fuel-air mixture, segments 15 are used which are active at low reaction temperatures. They are followed by further segments 15 of high oxidation effectiveness, in which the reaction temperature and thus the air heating increases. These catalytic segments are fastened in supporting structures and consist of a substrate and an intermediate adhesive layer, onto which the catalyst material from the platinum material group is evaporated. Due to the high operating temperatures of approx. 1450 ° K, high demands are placed on the materials. The porosity of the substrate using magnesium, aluminum and titanium alloys is set so that the pressure drop is small. A pressure loss of the entire combustion chamber of no more than 5% can be achieved if the substrate structure has at least 50 cells / cm².

Aus dem Katalysator 14 strömen die Reaktionsprodukte durch die Strömungsverengung 16 in die zweite Stufe 9 der Brennkammer 3. Die Strömungsverengung 16 hat die Aufgabe, Flammenrückschläge aus der zweiten Stufe der Brennkammer in den Katalysator, die zu seiner unweigerlichen Zerstörung führen würden, zu verhindern.The reaction products flow from the catalyst 14 through the flow restriction 16 into the second stage 9 of the combustion chamber 3. The flow restriction 16 has the task of preventing flashbacks from the second stage of the combustion chamber into the catalyst, which would lead to its inevitable destruction.

In die zweite Stufe 9 der Brennkammer 3 wird der Brennstoff mit Hilfe luftunterstützter Zerstäuberdüsen 17 eingeleitet. Neben den Zerstäuberdüsen 17 sind die Zündkerzen 18 zum Zünden des in der zweiten Stufe 9 befindlichen Brennstoff-Luft-Gemisches vorgesehen. Aufgrund des Aufbaus der Ringbrennkammer werden die Zerstäuberdüsen 17 auf der Innenwand der Brennkammer angeordnet und über innerhalb der Ringbrennkammer liegende Brennstoffversorgungsleitungen 19 mit Brennstoff versorgt. Diese zweigen von der Hauptbrennstoffleitung 20, an die die Vorverdampfer 10 angeschlossen sind, ab.The fuel is introduced into the second stage 9 of the combustion chamber 3 with the aid of air-assisted atomizing nozzles 17. In addition to the atomizing nozzles 17, the spark plugs 18 are provided for igniting the fuel-air mixture located in the second stage 9. Due to the structure of the annular combustion chamber, the atomizer nozzles 17 are arranged on the inner wall of the combustion chamber and are supplied with fuel via fuel supply lines 19 located within the annular combustion chamber. These branch off from the main fuel line 20 to which the pre-evaporators 10 are connected.

Die zweite Stufe 9 der Brennkammer 3 weist auf ihrem Umfang verteilt angeordnete Lufteinlaßöffnungen 21 und 22 auf, wobei die Lufteinlaßöffnungen 21 auf der Außenseite und die Lufteinlaßöffnungen 22 auf der Innenseite der ringförmigen Kopfbrennkammer angeordnet sind. Zur Steuerung der Luftzufuhr in die zweite Stufe der Brennkammer sind die inneren Lufteinlaßöffnungen 22 mit einem Lochring 23 versehen, welcher von einem Stellmotor 24 über Betätigungsglieder 25 gedreht werden kann. Sowohl der Stellmotor 24 als auch die Betätigungsglieder 25 können koaxial zur Längsachse 7 der Brennkammer angeordnet werden. Separate Wärmeisolationsmittel sind hier nicht notwendig, wenn der von der Ringbrennkammer umschlossene Innenraum aufgrund der zugeführten Luft gekühlt wird.The second stage 9 of the combustion chamber 3 has air inlet openings 21 and 22 distributed over its circumference, the air inlet openings 21 being arranged on the outside and the air inlet openings 22 being arranged on the inside of the annular head combustion chamber. To control the air supply to the second stage of the combustion chamber, the inner air inlet openings 22 are provided with a perforated ring 23 which can be rotated by an actuator 24 via actuators 25. Both the servomotor 24 and the actuators 25 can be arranged coaxially to the longitudinal axis 7 of the combustion chamber will. Separate heat insulation means are not necessary here if the interior enclosed by the annular combustion chamber is cooled due to the air supplied.

In Strömungsrichtung der Reaktionsprodukte am Ausgang der zweiten Stufe der Brennkammer 9 sind weitere Lufteinlaßöffnungen 26 und 27 auf dem inneren bzw. äußeren Umfang der Brennkammer verteilt angeordnet. Durch diese Lufteinlaßöffnungen 26 und 27 kann das geforderte Temperaturprofil am Brennkammeraustritt, insbesondere in deren Wandbereich, beeinflußt werden.In the direction of flow of the reaction products at the exit of the second stage of the combustion chamber 9, further air inlet openings 26 and 27 are arranged distributed on the inner and outer circumference of the combustion chamber. The required temperature profile at the combustion chamber outlet, in particular in its wall area, can be influenced by these air inlet openings 26 and 27.

Zum Starten der Gasturbinenanlage wird Brennstoff über die Leitungen 20 und 19 zu den luftummantelten Zerstäuberdüsen 17 geleitet. Gleichzeitig wird die Verdichterturbine über einen entsprechenden Anlassersatz beschleunigt, so daß verdichtete und mäßig erwärmte Luft über den noch kalten Wärmetauscher zu den Lufteinlaßöffnungen 12 sowie 21, 22 und 26, 27 in die erste und zweite Stufe der Brennkammer strömen kann. Da zum Starten der Gasturbinenanlage der Lochring 23 so eingestellt wird, daß der max. Öffnungsquerschnitt Lufteintrittsöffnung 22 freigegeben wird, kann sich dort ein brennfähiges Gemisch bilden, welches über die Zündeinrichtung 18 gezündet wird. Die dort eingeleitete Verbrennung bewirkt eine Erwärmung der Katalysatorsegmente 15 und liefert gleichzeitig erwärmte Reaktionsprodukte, die im Wärmetauscher 2 die von dem Verdichter 1 gelieferte verdichtete Luft weiter erwärmen.To start the gas turbine system, fuel is passed via lines 20 and 19 to the air-coated atomizer nozzles 17. At the same time, the compressor turbine is accelerated via a corresponding starter replacement, so that compressed and moderately heated air can flow via the still cold heat exchanger to the air inlet openings 12 and 21, 22 and 26, 27 into the first and second stages of the combustion chamber. Since the start of the gas turbine system, the perforated ring 23 is set so that the max. Opening cross section air inlet opening 22 is released, a combustible mixture can form there, which is ignited via the ignition device 18. The combustion initiated there heats up the catalyst segments 15 and at the same time supplies heated reaction products which further heat the compressed air supplied by the compressor 1 in the heat exchanger 2.

Sobald der Katalysator 14 seine Arbeitstemperatur erreicht hat, wird Brennstoff über die Vorverdampfer 10 in die erste Stufe 8 der Brennkammer eingeleitet. Damit liefert die Brennkammer Reaktionsprodukte, die sowohl die Verdichterturbine 4 als auch die Nutzturbine 5 antreiben können. Die Verbrennung wird in der zweiten Stufe 9 der Brennkammer nach dem Anlaufen des Gasturbinensatzes zurückgefahren, indem der Lochring 23 so verdreht wird, daß sich die Lufteinlaßöffnungen 22 verschließen. Jedoch wird durch luftummantelten Verstäuberdüsen 17 weiterhin eine geringe Menge Brennstoff zugeführt, so daß dort eine Art Pilotflamme aufrechterhalten wird.As soon as the catalytic converter 14 has reached its working temperature, fuel is introduced into the first stage 8 of the combustion chamber via the pre-evaporators 10. The combustion chamber thus supplies reaction products that both the compressor turbine 4 and the utility turbine 5 can drive. The combustion is reduced in the second stage 9 of the combustion chamber after the start of the gas turbine set by rotating the perforated ring 23 so that the air inlet openings 22 close. However, a small amount of fuel is still supplied through air-coated atomizing nozzles 17, so that a kind of pilot flame is maintained there.

Zum Beschleunigen des von dem Gasturbinensatz angetriebenen Fahrzeuges wird in der zweiten Stufe der Brennkammer 3 die Luftzufuhr über den Lochring 23 sowie der Brennstoffzufuhr über die Zerstäuberdüsen 17 wieder erhöht, so daß hier eine merkliche Nachverbrennung stattfindet und damit eine merkliche Temperaturerhöhung. Ebenso wird dies bei Vollast durchgeführt.In order to accelerate the vehicle driven by the gas turbine set, the air supply via the perforated ring 23 and the fuel supply via the atomizing nozzles 17 are increased again in the second stage of the combustion chamber 3, so that a noticeable afterburning takes place and thus a noticeable increase in temperature. This is also done at full load.

Claims (20)

1. A gas turbine plant, more particularly for driving motor vehicles, comprising a combustion chamber (3) for producing the medium for actuating the work turbine (5), the combustion chamber (3) being a two-stage combustion chamber with catalytic combustion in the first stage (8) which is in the form of a topped combustion chamber, characterised in that the combustion chamber (3) is an annular combustion chamber comprising an annular catalyzer (14), and the inner wall of the combustion chamber (3) forms a closed inner chamber which is coaxial with the axis (7) of the combustion chamber (3) and which contains the conduits (19, 25) for supplying fuel and combustion air to the second stage (9) of the combustion chamber (3).
2. A gas turbine plant according to claim 1, characterised in that a flow constriction (16) in the direction of the second stage (9) is provided between the first stage (8) and the second stage (9) of the combustion chamber (3).
3. A gas turbine plant according to claim 1 or 2, characterised in that the fuel is introduced into the first stage (8) via a pre-evaporator (10).
4. A gas turbine plant according to any of the preceding claims, characterised in that the combustion chamber (3) in the first stage (8) is made up of a premixing zone (13) based on the diffusion-burner principle and a combustion zone and catalyzer (14) ― in this order when considered in the direction of flow of the air.
5. A gas turbine plant according to any of the preceding claims, characterised in that the catalyzer (14) is made up of a number of annular individual disc segments (15).
6. A gas turbine plant according to any of the preceding claims, characterised in that, in the direction of flow of the fuel-air mixture, the segments having a lower reaction temperature are placed first, followed by the segments having a higher reaction temperature.
7. A gas turbine plant according to any of the preceding claims, characterised in that the segments comprise a substrate, an intermediate adhesive layer, and a catalyst layer disposed thereon.
8. A gas turbine plant according to claim 7, characterised in that the substrate comprises alloys of magnesium, aluminium and titanium.
9. A gas turbine plant according to claim 7, characterised in that the catalyst is of materials from the platinum group.
10. A gas turbine plant according to any of the preceding claims, characterised in that, to reduce the pressure loss, each catalyzer segment contains at least 50 cells per cm².
11. A gas turbine plant according to any of the preceding claims, characterised in that the second stage (9) of the combustion chamber (3) has air inlets (22) which can be actuated and adjusted.
12. A gas turbine plant according to any of the preceding claims, characterised in that the air inlets (22) are actuated by a servomotor (24) and actuating components (25) disposed along the longitudinal axis (7) of the annular combustion chamber (3).
13. A gas turbine plant according to claim 12, characterised in that the size of the air inlets (22) is determined by a rotatable orifice ring (23).
14. A gas turbine plant according to claim 12, characterised in that the size of the air inlets (22) is determined by a movable ring.
15. A gas turbine plant according to any of the preceding claims, characterised in that air inlets (21, 22, 26, 27) are disposed on the inner and outer periphery of the second stage (9) of the combustion chamber (3) and only the inner air inlets (22) are provided with a ring (orifice ring 23).
16. A gas turbine plant according to any of the preceding claims, characterised in that at least one air-assisted atomizer nozzle (17) is provided for introducing the fuel into the second stage (9).
17. A gas turbine plant according to any of the preceding claims, characterised in that a spark plug (18) is provided in the immediate neighbourhood of the atomizer nozzle (17).
18. A method of operating the gas turbine plant according to at least one of the preceding claims, characterised in that, in order to start the internal combustion engine, combustion is initiated in the second stage.
19. A method according to claim 18, characterised in that the air supply in the second stage of the combustion chamber is controlled in dependence on the air required in the catalyzer.
20. A method according to any of the preceding claims, characterised in that, during acceleration and under full load, the power delivery of the second stage of the combustion chamber is increased.
EP88120316A 1987-12-17 1988-12-06 Gas turbine plant Expired - Lifetime EP0320746B1 (en)

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DE3742891 1987-12-17
DE19873742891 DE3742891A1 (en) 1987-12-17 1987-12-17 GAS TURBINE SYSTEM

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EP0320746B1 true EP0320746B1 (en) 1991-09-25

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ES2026244T3 (en) 1992-04-16
US5003768A (en) 1991-04-02
EP0320746A1 (en) 1989-06-21
DE3865188D1 (en) 1991-10-31
DE3742891A1 (en) 1989-06-29

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