EP2157286A1 - Gas turbine comprising angled duct and method for guiding the flow onto the turbine - Google Patents

Gas turbine comprising angled duct and method for guiding the flow onto the turbine Download PDF

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Publication number
EP2157286A1
EP2157286A1 EP08014874A EP08014874A EP2157286A1 EP 2157286 A1 EP2157286 A1 EP 2157286A1 EP 08014874 A EP08014874 A EP 08014874A EP 08014874 A EP08014874 A EP 08014874A EP 2157286 A1 EP2157286 A1 EP 2157286A1
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EP
European Patent Office
Prior art keywords
inner housing
turbine
housing
mixing
combustion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP08014874A
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German (de)
French (fr)
Inventor
Andre Botzen
Karl Dr. Klein
Marco Link
Oliver Dr. Lüsebrink
Nicolas Savilius
Oliver Dr. Schneider
Marc Tertilt
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Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08014874A priority Critical patent/EP2157286A1/en
Publication of EP2157286A1 publication Critical patent/EP2157286A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the present invention relates to a gas turbine arrangement comprising at least one burner and a combustion chamber for combusting fuel, a mixing housing and an adjoining inner housing and a turbine arranged substantially in relation to the at least one burner, wherein the combustion exhaust gas resulting from the combustion of the fuel flows through the mixing housing in the inner housing, wherein the inner housing is configured such that the combustion exhaust gas is deflected in the inner housing in the direction of the turbine. Furthermore, the invention relates to a gas turbine and a method for Turbinenanströmung.
  • a gas turbine plant 1 essentially comprises one or more combustion chambers 3 with burners 13 (cf. FIG. 2 ), in which a fuel is burned, a turbine 5, which are supplied to the hot and pressurized combustion exhaust gases from the combustion chambers 3 and in which the exhaust work under cooling and relaxation work and so put the turbine 5 in rotation, and a compressor 7, which is coupled to the turbine 5 via a shaft 12 which is surrounded by a hub 17, and via which the air necessary for the combustion is sucked in and compressed to a higher pressure.
  • FIG. 1 shows such a gas turbine plant in a schematic view, wherein FIG1 shows a horizontal section through the plant.
  • the combustion gases 2 flow in a direction which is substantially perpendicular to a rotation axis A of the turbine 5.
  • a mixing housing 8 is arranged, which is adjoined on the turbine side by an inner housing 9 arranged in the interior of the gas turbine housing 2.
  • the inner housing 9 has the task to protect the surrounding components from heat and to redirect the exiting the mixing housing 8 hot exhaust gases in the direction of the turbine 5.
  • the gas in the inner housing 9 is deflected substantially by 90 ° degrees and then fed via a common annular space of the turbine. Due to the shape of the housing, there is no clear guidance of the two gas streams from the two silo separation chambers 3 to the turbine 5, that is to say the streams impinge on the hub 17 and are then distributed over the surrounding space to the turbine inlet. This results in an inhomogeneous flow of the turbine 5. This is to be expected with performance losses.
  • the first object is achieved by a gas turbine arrangement according to claim 1.
  • the object related to the gas turbine is solved by specifying a gas turbine according to claim 5.
  • the object related to the method is solved by claim 6.
  • the dependent claims contain advantageous embodiments of the invention.
  • a gas turbine arrangement comprises at least one burner and a combustion chamber for combusting fuel, a mixing housing and an adjoining inner housing and a turbine, which is arranged vertically with respect to the at least one burner.
  • the combustion exhaust gas produced by the combustion of the fuel flows through the mixing housing into the inner housing, wherein the inner housing is designed such that the combustion exhaust gas is deflected in the inner housing in the direction of the turbine. This is essentially a 90 degree deflection. Since, due to the shape of the housing, no clear guidance of the gas flow to the turbine, there is an inhomogeneous flow. This results in poor performance values.
  • the invention intervenes, and solves this long-standing problem by the mixing housing is angled relative to the inner housing, so that a better deflection of the combustion exhaust gas is effected in the direction of the turbine.
  • the mixing housing namely the exhaust gas is better redirected in the inner housing.
  • the gas turbine arrangement comprises a shaft on which the turbine is arranged.
  • the inner housing has an inner housing hub, which is arranged substantially parallel to the shaft.
  • This inner housing hub is preferably at least approximately cylindrical.
  • the angle between the inner housing and the mixing housing is designed such that Strömungsstaulie in the inner housing and on the Inner housing hub are avoided. This avoids the wear of these components due to oxidation and erosion.
  • a gas turbine which comprises at least two burners and combustion chambers that are substantially opposite each other.
  • This can be especially known Silobrennschn.
  • the mixing housing a and b and an inner housing with a arranged around a shaft closed inner housing hub.
  • an annular space is formed with a circumference.
  • the mixing housing a and b are now angled in the circumferential direction. As a result, both a better deflection and an improved flow of the turbine is achieved.
  • a method for turbine flow which comprises a burner and a combustion chamber in which fuel is combusted to combustion exhaust gases, and a mixing housing and an adjoining inner housing for guiding the combustion exhaust gases to a turbine which is substantially perpendicular to the flow direction of the Combustion gases is arranged in the combustion chamber, wherein the combustion gases are deflected toward the turbine in the inner housing, wherein by means of angling the mixing housing relative to the inner housing, the flow diversion is improved in the inner housing, so that an improved turbine flow is achieved.
  • the flow diversion of the exhaust gases in the inner housing is improved, which leads to a homogenization of the hot gas flow in the inner housing.
  • the flow to the turbine is made uniform, thereby improving the performance of the machine. Also Strömungsstauains be avoided in the inner housing and the hub, resulting in less wear.
  • gas turbine plant 1 An example of gas turbine plant 1 is in the FIG. 1 shown in a highly schematic representation.
  • the gas turbine plant 1 comprises two silo combustion chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9.
  • the silo combustion chambers 3 serve for burning a fuel, the hot exhaust gases 2 under high pressure being supplied via the mixing housings 8 and the inner housing 9 of the turbine 5 are supplied to drive these.
  • the turbine 5 comprises stationary guide vanes 10 and rotor blades 11 fixedly connected to a shaft 12 rotatably mounted about an axis A.
  • the hot exhaust gas 2 expanding in the turbine 5 transmits impulse to the shaft 12 via the rotor blades 11, causing them to rotate becomes.
  • the shaft 12 can be roughly divided into three sections, namely a section carrying the blades 11 of the turbine 5, a rotor blade of the compressor 7 (not shown) and a shaft section 16 arranged between these two sections, in which no blades are arranged.
  • the shaft 12 and the attached blades 11 form the so-called. Turbine rotor.
  • the shaft 12 extends through the entire gas turbine plant (not fully shown) and drives the compressor 7 and a generator, not shown.
  • the compressor 7 serves to compress air, which is then fed to the silo combustion chambers 3 for combustion.
  • FIG. 2 shows a vertical section through the silo combustion chamber 3 with burners 13 a subsequent mixing housing 8 and an inner housing 9.
  • the combustion chamber 3 as the burner 13 are vertical and are located at the top of the figure shown.
  • the conical and curved mixing housing connects, which leads the combustion exhaust gases to the inner housing 9.
  • the shaft 12 is of a wave protection jacket 15 (see. FIG. 3 ), which itself is surrounded by an inner housing hub 17 of the inner housing 9.
  • FIG. 3 shows the inner housing with inner housing hub 17 (vertical section through the inner housing), in which the inner housing hub 17 of the inner housing 9 and a part of the wave protection jacket 15 can be seen.
  • a guide vane 10 of the turbine 5 can be seen, which is opposite to the turbine-side opening 19 of the inner housing 9.
  • the inner housing hub 17 and the shaft protection jacket 15 have substantially the shape of a hollow cylinder.
  • the inner housing 9 serves to deflect the hot exhaust flowing from the mixing housings 8 into the inner housing 9 on the one hand and to distribute it as evenly as possible around the entire circumference of the turbine runner on the other hand. Here, the deflection is done by about 90 ° degrees.
  • the gases are then fed to the turbine 5 via a common annular space. Due to the shape of the mixing housing 8, there is no clear guidance of the two Exhaust gas flows to the turbine, that is, the currents meet at the level of a parting line (not shown) on the hub 17 and then distributed to the circumferential space to the turbine inlet 20. This results in an inhomogeneous flow to the turbine 5, which is expected to performance losses is.
  • FIG. 4 schematically shows an inner housing 9 and the inner housing hub 17 and the turbine inlet 20.
  • the inner housing 9 and the hub 17 thereby form an annular space with a circumference in which the flow flows.
  • the mixing housing 80a and 80b according to the invention is angled relative to the inner housing 9 shown here in the circumferential direction. As a result, the combustion exhaust gas stream 22 is better diverted.
  • the angling of the mixing housings 80a, b improves the flow diversion in the inner housing 9, which leads to the avoidance of flow accumulation points in the inner housing 9 and on the hub 17.
  • the wear of the components is reduced by oxidation and erosion.
  • the combustion exhaust gas flow 22 is improved in the inner housing 9, which leads to a homogenization of the flow in the inner housing 9. This improves the flow of the turbine 5 and there is an improvement in the performance values.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The arrangement has a burner, and a combustion chamber for combustion of fuel. An inner housing (9) is arranged adjacent to mixing housings (80a, 80b). A turbine is arranged perpendicular with respect to the burner. A combustion exhaust gas resulting by the combustion of the fuel flows into the inner housing through the mixing housings. The inner housing is designed in such a manner that the exhaust gas in the inner housing is deflected toward the turbine. The mixing housings are angled opposite to the inner housing. An independent claim is also included for a method for improving turbine inflow.

Description

Die vorliegende Erfindung betrifft eine Gasturbinenanordnung umfassend zumindest einem Brenner und einer Brennkammer zum Verbrennen von Brennstoff, einem Mischgehäuse sowie einem sich daran anschließenden Innengehäuse und einer im wesentlichen in Bezug auf den zumindest einen Brenner senkrecht angeordneten Turbine, wobei das durch das verbrennen des Brennstoffs entstehende Verbrennungsabgas durch das Mischgehäuse in das Innengehäuse strömt, wobei das Innengehäuse derart ausgestaltet ist, dass das Verbrennungsabgas im Innengehäuse in Richtung Turbine umgelenkt wird. Weiterhin betrifft die Erfindung eine Gasturbine und ein Verfahren zur Turbinenanströmung.The present invention relates to a gas turbine arrangement comprising at least one burner and a combustion chamber for combusting fuel, a mixing housing and an adjoining inner housing and a turbine arranged substantially in relation to the at least one burner, wherein the combustion exhaust gas resulting from the combustion of the fuel flows through the mixing housing in the inner housing, wherein the inner housing is configured such that the combustion exhaust gas is deflected in the inner housing in the direction of the turbine. Furthermore, the invention relates to a gas turbine and a method for Turbinenanströmung.

Eine Gasturbinenanlage 1 (vgl. FIG 1) umfasst im Wesentlichen eine oder mehrere Brennkammern 3 mit Brennern 13 (vgl. FIG 2), in denen ein Brennstoff verbrannt wird, eine Turbine 5, der die heißen und unter Druck stehenden Verbrennungsabgase aus den Brennkammern 3 zugeführt werden und in der die Abgase unter Abkühlung und Entspannung Arbeit leisten und so die Turbine 5 in Rotation versetzen, sowie einen Verdichter 7, der mit der Turbine 5 über eine Welle 12, welche von einer Nabe 17 umgeben ist, gekoppelt ist und über den die für die Verbrennung notwendige Luft eingesaugt und auf einen höheren Druck verdichtet wird.A gas turbine plant 1 (see. FIG. 1 ) essentially comprises one or more combustion chambers 3 with burners 13 (cf. FIG. 2 ), in which a fuel is burned, a turbine 5, which are supplied to the hot and pressurized combustion exhaust gases from the combustion chambers 3 and in which the exhaust work under cooling and relaxation work and so put the turbine 5 in rotation, and a compressor 7, which is coupled to the turbine 5 via a shaft 12 which is surrounded by a hub 17, and via which the air necessary for the combustion is sucked in and compressed to a higher pressure.

Zum Führen der heißen Verbrennungsabgase kommen in Gasturbinenanlagen heißgasführenden Bauteile wie Mischgehäuse und Innengehäuse zum Einsatz. Dies trifft insbesondere für solche Gasturbinenanlagen zu, in denen so genannte Silobrennkammern 3 Verwendung finden, die in der Regel zu beiden Seiten der Turbine 5 angeordnet sind.To guide the hot combustion gases are used in gas turbine plants hot gas components such as mixing housing and inner housing used. This is especially true for such gas turbine plants, in which so-called silo separation chambers 3 are used, which are usually arranged on both sides of the turbine 5.

FIG 1 zeigt eine derartige Gasturbinenanlage in einer schematischen Ansicht, wobei FIG1 einen horizontalen Schnitt durch die Anlage zeigt. FIG. 1 shows such a gas turbine plant in a schematic view, wherein FIG1 shows a horizontal section through the plant.

Aus diesen Silobrennkammern 3 strömen die Verbrennungsabgase 2 in einer Richtung aus, die im Wesentlichen senkrecht zu einer Drehachse A der Turbine 5 verläuft. Zwischen dem Ausgang 18 der Silobrennkammern 3 und der Turbine 5 ist ein Mischgehäuse 8 angeordnet, dem sich turbinenseitig ein im Inneren des Gasturbinengehäuses 2 angeordnetes Innengehäuse 9 anschließt. Das Innengehäuse 9 hat die Aufgabe, die umgebenden Bauteile vor Hitze zu schützen und die aus dem Mischgehäuse 8 austretenden heißen Abgase in Richtung auf die Turbine 5 umzulenken. Beim Austritt aus dem Innengehäuse 9, das heißt beim Eintritt in die Turbine 5 der Gasturbinenanlage 1 strömen die Verbrennungsabgase dann im Wesentlichen parallel zur Rotationsachse A der Turbinenwelle 12.From these Silobrennkammern 3, the combustion gases 2 flow in a direction which is substantially perpendicular to a rotation axis A of the turbine 5. Between the outlet 18 of the silo separation chambers 3 and the turbine 5, a mixing housing 8 is arranged, which is adjoined on the turbine side by an inner housing 9 arranged in the interior of the gas turbine housing 2. The inner housing 9 has the task to protect the surrounding components from heat and to redirect the exiting the mixing housing 8 hot exhaust gases in the direction of the turbine 5. When exiting the inner housing 9, that is to say when entering the turbine 5 of the gas turbine plant 1, the combustion exhaust gases then flow essentially parallel to the axis of rotation A of the turbine shaft 12.

Beim Zuführen des Gases zur Turbine 5 wird das Gas im Innengehäuse 9 im Wesentlichen um 90 ° Grad umgelenkt und anschließend über einen gemeinsamen Ringraum der Turbine zugeführt. Bedingt durch die Form des Gehäuses erfolgt keine eindeutige Führung der beiden Gasströme aus den beiden Silobrennkammern 3 auf die Turbine 5, das heißt die Ströme treffen auf die Nabe 17 und verteilen sich dann auf den umlaufenden Raum zum Turbineneintritt. Dadurch ergibt sich eine inhomogene Anströmung der Turbine 5. Daraus ist mit Performanceverlusten zu rechnen.When supplying the gas to the turbine 5, the gas in the inner housing 9 is deflected substantially by 90 ° degrees and then fed via a common annular space of the turbine. Due to the shape of the housing, there is no clear guidance of the two gas streams from the two silo separation chambers 3 to the turbine 5, that is to say the streams impinge on the hub 17 and are then distributed over the surrounding space to the turbine inlet. This results in an inhomogeneous flow of the turbine 5. This is to be expected with performance losses.

Gegenüber diesem Stand der Technik ist es eine Aufgabe der vorliegenden Erfindung, eine verbesserte Gasturbinenanordnung zur Verfügung zu stellen, welche eine verbesserte Turbinenanströmung gewährleistet. Eine weitere Aufgabe ist die Angabe einer solchen Gasturbine. Eine weitere Aufgabe ist die Angabe eines Verfahrens, welchem eine verbesserte Turbinenanströmung zugrunde liegt.Compared to this prior art, it is an object of the present invention to provide an improved gas turbine assembly which ensures improved turbine flow. Another task is the specification of such a gas turbine. Another object is to specify a method based on improved turbine flow.

Die erste Aufgabe wird durch eine Gasturbinenanordnung nach Anspruch 1 gelöst. Die auf die Gasturbine bezogene Aufgabe wird durch die Angabe einer Gasturbine nach Anspruch 5 gelöst. Die auf das Verfahren bezogene Aufgabe wird durch Anspruch 6 gelöst. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by a gas turbine arrangement according to claim 1. The object related to the gas turbine is solved by specifying a gas turbine according to claim 5. The object related to the method is solved by claim 6. The dependent claims contain advantageous embodiments of the invention.

Eine erfindungsgemäße Gasturbinenanordnung umfasst zumindest einen Brenner und eine Brennkammer zum Verbrennen von Brennstoff, ein Mischgehäuse sowie ein sich daran anschließendes Innengehäuse und eine, im Wesentlichen in Bezug auf den zumindest einen Brenner senkrecht angeordneten Turbine. Dabei strömt das durch das verbrennen des Brennstoffs entstehende Verbrennungsabgas durch das Mischgehäuse in das Innengehäuse, wobei das Innengehäuse derart ausgestaltet ist, dass das Verbrennungsabgas im Innengehäuse in Richtung Turbine umgelenkt wird. Dies ist im Wesentlichen eine Ablenkung um 90 °Grad. Da, bedingt durch die Form des Gehäuses, keine eindeutige Führung des Gasstroms auf die Turbine erfolgt, ergibt sich eine inhomogene Anströmung. Daraus resultieren schlechte Performancewerte. Hier greift nun die Erfindung ein, und löst dieses lang bestehende Problem, indem das Mischgehäuse gegenüber dem Innengehäuse angewinkelt ist, so dass eine bessere Umlenkung des Verbrennungsabgases in Richtung Turbine bewirkt ist. Durch das Anwinkeln des Mischgehäuses nämlich wird das Abgas im Innengehäuse besser umgeleitet. Dadurch resultiert eine Vergleichmäßigung der Abgasströmung im Innengehäuse, wodurch die Turbine besser angeströmt wird. Dadurch ist es beispielsweise möglich, die einzelnen Turbinenschaufeln gemäß ihrer Auslegung anzuströmen.A gas turbine arrangement according to the invention comprises at least one burner and a combustion chamber for combusting fuel, a mixing housing and an adjoining inner housing and a turbine, which is arranged vertically with respect to the at least one burner. In this case, the combustion exhaust gas produced by the combustion of the fuel flows through the mixing housing into the inner housing, wherein the inner housing is designed such that the combustion exhaust gas is deflected in the inner housing in the direction of the turbine. This is essentially a 90 degree deflection. Since, due to the shape of the housing, no clear guidance of the gas flow to the turbine, there is an inhomogeneous flow. This results in poor performance values. Here, the invention intervenes, and solves this long-standing problem by the mixing housing is angled relative to the inner housing, so that a better deflection of the combustion exhaust gas is effected in the direction of the turbine. By the angling of the mixing housing namely the exhaust gas is better redirected in the inner housing. This results in a homogenization of the exhaust gas flow in the inner housing, whereby the turbine is better flowed. This makes it possible, for example, to flow to the individual turbine blades according to their design.

Die Gasturbinenanordnung umfasst dabei eine Welle an der die Turbine angeordnet ist. Das Innengehäuse weist eine Innengehäusenabe auf, welche im Wesentlichen parallel zur Welle angeordnet ist. Diese Innengehäusenabe ist bevorzugt wenigstens näherungsweise zylindrisch ausgebildet. Bevorzugt ist der Winkel zwischen Innengehäuse und Mischgehäuse derart ausgebildet, dass Strömungsstaupunkte im Innengehäuse und an der Innengehäusenabe vermieden sind. Dadurch wird der Verschleiß dieser Bauteile durch Oxidation und Erosion vermieden.The gas turbine arrangement comprises a shaft on which the turbine is arranged. The inner housing has an inner housing hub, which is arranged substantially parallel to the shaft. This inner housing hub is preferably at least approximately cylindrical. Preferably, the angle between the inner housing and the mixing housing is designed such that Strömungsstaupunkte in the inner housing and on the Inner housing hub are avoided. This avoids the wear of these components due to oxidation and erosion.

Erfindungsgemäß wird weiterhin eine Gasturbine offenbart, welche zumindest zwei sich im Wesentlichen gegenüberliegende Brenner und Brennkammern umfasst. Dies können vor allem bekannte Silobrennkammern sein. An diese schließen sich jeweils die Mischgehäuse a und b sowie ein Innengehäuse mit einer um eine Welle angeordneten geschlossenen Innengehäusenabe an. Durch das Innengehäuse und die Nabe wird ein Ringraum mit einem Umfang ausgebildet. Erfindungsgemäß sind nun das Mischgehäuse a und b in Umfangsrichtung angewinkelt. Dadurch wird sowohl eine bessere Umlenkung als auch eine verbesserte Anströmung der Turbine erzielt.According to the invention, furthermore, a gas turbine is disclosed, which comprises at least two burners and combustion chambers that are substantially opposite each other. This can be especially known Silobrennkammern. These are followed in each case by the mixing housing a and b and an inner housing with a arranged around a shaft closed inner housing hub. Through the inner housing and the hub, an annular space is formed with a circumference. According to the mixing housing a and b are now angled in the circumferential direction. As a result, both a better deflection and an improved flow of the turbine is achieved.

Erfindungsgemäß wird weiterhin ein Verfahren zur Turbinenanströmung offenbart, welche einen Brenner und eine Brennkammer, in welcher Brennstoff zu Verbrennungsabgasen verbrannt wird, umfasst, und ein Mischgehäuse sowie ein sich daran anschließendes Innengehäuse zum Führen der Verbrennungsabgase zu einer Turbine, die im wesentlichen senkrecht zur Strömungsrichtung der Verbrennungsabgase in der Brennkammer angeordnet ist, wobei im Innengehäuse die Verbrennungsabgase in Richtung Turbine abgelenkt werden, wobei mittels anwinkeln des Mischgehäuses gegenüber dem Innengehäuse die Strömungsumleitung im Innengehäuse verbessert wird, so dass eine verbesserte Turbinenanströmung erzielt wird. Dadurch wird die Strömungsumleitung der Abgase im Innengehäuse verbessert, was zu einer Vergleichmäßigung der Heißgasströmung im Innengehäuse führt. Dadurch vergleichmäßigt sich die Anströmung auf die Turbine, wodurch eine Verbesserung der Performancewerte der Maschine erzielt wird. Auch werden Strömungsstaupunkte im Innengehäuse und an der Nabe vermieden, was zu einem geringeren Verschleiß führt.According to the invention, a method for turbine flow is further disclosed, which comprises a burner and a combustion chamber in which fuel is combusted to combustion exhaust gases, and a mixing housing and an adjoining inner housing for guiding the combustion exhaust gases to a turbine which is substantially perpendicular to the flow direction of the Combustion gases is arranged in the combustion chamber, wherein the combustion gases are deflected toward the turbine in the inner housing, wherein by means of angling the mixing housing relative to the inner housing, the flow diversion is improved in the inner housing, so that an improved turbine flow is achieved. As a result, the flow diversion of the exhaust gases in the inner housing is improved, which leads to a homogenization of the hot gas flow in the inner housing. As a result, the flow to the turbine is made uniform, thereby improving the performance of the machine. Also Strömungsstaupunkte be avoided in the inner housing and the hub, resulting in less wear.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren.

FIG 1
zeigt einen horizontalen Schnitt durch eine Gasturbinenanlage mit zwei Silobrennkammern in einer stark schematisierten Darstellung nach dem Stand der Technik,
FIG 2
zeigt einen vertikalen Schnitt einer Silobrennkammer, dem Mischgehäuse und dem Innengehäuse nach dem Stand der Technik,
FIG 3
zeigt einen Ausschnitt eines Innengehäuses und zugehöriger Innengehäusenabe nach dem Stand der Technik,
FIG 4
zeigt schematisch das erfindungsgemäße angewinkelte Mischgehäuse mit Innengehäuse.
Further features, properties and advantages of the present invention will become apparent from the following description of Embodiments with reference to the accompanying figures.
FIG. 1
shows a horizontal section through a gas turbine plant with two Silobrennkammern in a highly schematic representation of the prior art,
FIG. 2
shows a vertical section of a silo combustion chamber, the mixing housing and the inner housing according to the prior art,
FIG. 3
shows a section of an inner housing and associated inner housing hub according to the prior art,
FIG. 4
schematically shows the angled mixing housing according to the invention with inner housing.

Ein Beispiel für Gasturbinenanlage 1 ist in der Figur 1 in einer stark schematisierten Darstellung gezeigt. Die Gasturbinenanlage 1 umfasst zwei Silobrennkammern 3, eine Turbine 5, einen Verdichter 7, zwei Mischgehäuse 8 sowie ein Innengehäuse 9. Die Silobrennkammern 3 dienen zum Verbrennen eines Brennstoffes, wobei die heißen und unter hohem Druck stehenden Abgase 2 über die Mischgehäuse 8 und das Innengehäuse 9 der Turbine 5 zugeführt werden, um diese anzutreiben.An example of gas turbine plant 1 is in the FIG. 1 shown in a highly schematic representation. The gas turbine plant 1 comprises two silo combustion chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9. The silo combustion chambers 3 serve for burning a fuel, the hot exhaust gases 2 under high pressure being supplied via the mixing housings 8 and the inner housing 9 of the turbine 5 are supplied to drive these.

Die Turbine 5 umfasst stationäre Leitschaufeln 10 sowie mit einer um eine Achse A drehbar gelagerten Welle 12 fest verbundene Laufschaufeln 11. Durch das in der Turbine 5 expandierende heiße Abgas 2 wird Impuls über die Laufschaufeln 11 auf die Welle 12 übertragen, wodurch diese in Rotation versetzt wird.The turbine 5 comprises stationary guide vanes 10 and rotor blades 11 fixedly connected to a shaft 12 rotatably mounted about an axis A. The hot exhaust gas 2 expanding in the turbine 5 transmits impulse to the shaft 12 via the rotor blades 11, causing them to rotate becomes.

Die Welle 12 kann grob in drei Abschnitte unterteilt werden, nämlich einen die Laufschaufeln 11 der Turbine 5 tragenden Abschnitt, einen Laufschaufeln des Verdichters 7 (nicht dargestellt) tragenden Abschnitt sowie einen zwischen diesen beiden Abschnitten angeordneten Wellenabschnitt 16, in dem keine Laufschaufeln angeordnet sind. Die Welle 12 und die daran angebrachten Laufschaufeln 11 bilden den sog. Turbinenläufer.The shaft 12 can be roughly divided into three sections, namely a section carrying the blades 11 of the turbine 5, a rotor blade of the compressor 7 (not shown) and a shaft section 16 arranged between these two sections, in which no blades are arranged. The shaft 12 and the attached blades 11 form the so-called. Turbine rotor.

Die Welle 12 erstreckt sich durch die gesamte Gasturbinenanlage (nicht vollständig dargestellt) und treibt den Verdichter 7 sowie einen nicht dargestellten Generator an. Der Verdichter 7 dient dabei dazu, Luft zu verdichten, die anschließend den Silobrennkammern 3 für die Verbrennung zugeführt wird.The shaft 12 extends through the entire gas turbine plant (not fully shown) and drives the compressor 7 and a generator, not shown. The compressor 7 serves to compress air, which is then fed to the silo combustion chambers 3 for combustion.

FIG 2 zeigt einen vertikalen Schnitt durch die Silobrennkammer 3 mit Brennern 13 einem sich anschließendem Mischgehäuse 8 und einem Innengehäuses 9. Die Brennkammer 3 wie die Brenner 13 verlaufen vertikal und befinden sich am oberen Ende der gezeigten Figur. An das untere Ende der Brennkammer 3 schließt sich das konische und gekrümmte Mischgehäuse an, das die Verbrennungsabgase zu dem Innengehäuse 9 führt. FIG. 2 shows a vertical section through the silo combustion chamber 3 with burners 13 a subsequent mixing housing 8 and an inner housing 9. The combustion chamber 3 as the burner 13 are vertical and are located at the top of the figure shown. At the lower end of the combustion chamber 3, the conical and curved mixing housing connects, which leads the combustion exhaust gases to the inner housing 9.

Die Welle 12 ist von einem Wellenschutzmantel 15 (vgl. FIG 3) umgeben, welche selbst von einer Innengehäusenabe 17 des Innengehäuses 9 umgeben ist.The shaft 12 is of a wave protection jacket 15 (see. FIG. 3 ), which itself is surrounded by an inner housing hub 17 of the inner housing 9.

FIG 3 zeigt das Innengehäuse mit Innengehäusenabe 17 (vertikaler Schnitt durch das Innengehäuse), in dem die Innengehäusenabe 17 des Innengehäuses 9 sowie ein Teil des Wellenschutzmantels 15 zu erkennen sind. Ausschnittsweise ist auch eine Leitschaufel 10 der Turbine 5 zu erkennen, die der turbinenseitigen Öffnung 19 des Innengehäuses 9 gegenüberliegt. FIG. 3 shows the inner housing with inner housing hub 17 (vertical section through the inner housing), in which the inner housing hub 17 of the inner housing 9 and a part of the wave protection jacket 15 can be seen. In sections, a guide vane 10 of the turbine 5 can be seen, which is opposite to the turbine-side opening 19 of the inner housing 9.

Die Innengehäusenabe 17 sowie der Wellenschutzmantel 15 haben im Wesentlichen die Form eines Hohlzylinders. Das Innengehäuse 9 dient dazu, das aus den Mischgehäusen 8 in das Innengehäuse 9 einströmende heiße Abgas einerseits abzulenken und andererseits möglichst gleichmäßig um den gesamten Umfang des Turbinenläufers zu verteilen. Hierbei erfolgt die Ablenkung um ca. 90 °Grad. Über einen gemeinsamen Ringraum werden die Gase dann der Turbine 5 zugeführt. Bedingt durch die Form des Mischgehäuses 8 erfolgt keine eindeutige Führung der beiden Abgasströme auf die Turbine, das heißt die Ströme treffen in Höhe einer Teilfuge (nicht gezeigt) auf die Nabe 17 und verteilen sich dann auf den umlaufenden Raum zum Turbineneintritt 20. Dadurch ergibt sich eine inhomogene Anströmung auf die Turbine 5, wodurch mit Performanceverlusten zu rechnen ist.The inner housing hub 17 and the shaft protection jacket 15 have substantially the shape of a hollow cylinder. The inner housing 9 serves to deflect the hot exhaust flowing from the mixing housings 8 into the inner housing 9 on the one hand and to distribute it as evenly as possible around the entire circumference of the turbine runner on the other hand. Here, the deflection is done by about 90 ° degrees. The gases are then fed to the turbine 5 via a common annular space. Due to the shape of the mixing housing 8, there is no clear guidance of the two Exhaust gas flows to the turbine, that is, the currents meet at the level of a parting line (not shown) on the hub 17 and then distributed to the circumferential space to the turbine inlet 20. This results in an inhomogeneous flow to the turbine 5, which is expected to performance losses is.

FIG 4 zeigt schematisch ein Innengehäuse 9 sowie die Innengehäusenabe 17 und den Turbineneintritt 20. Das Innengehäuse 9 und die Nabe 17 bilden dabei einen Ringraum mit einem Umfang in dem die Strömung einströmt. Das erfindungsgemäße Mischgehäuse 80a und 80b ist gegenüber dem Innengehäuse 9 angewinkelt hier gezeigt in Umfangsrichtung angewinkelt. Dadurch wird der Verbrennungsabgasstrom 22 besser umgeleitet. Durch das Anwinkeln der Mischgehäuse 80a,b wird die Strömungsumleitung im Innengehäuse 9 verbessert, was zur Vermeidung von Strömungsstaupunkten im Innengehäuse 9 und an der Nabe 17 führt. Dadurch wird der Verschleiß der Bauteile durch Oxidation und Erosion vermindert. Weiterhin wird die Verbrennungsabgasströmung 22 im Innengehäuse 9 verbessert, was zu einer Vergleichmäßigung der Strömung im Innengehäuse 9 führt. Dadurch verbessert sich die Anströmung der Turbine 5 und es kommt zu einer Verbesserung der Performancewerte. Mittels der Erfindung ist es nun möglich, die einzelnen Turbinenschaufeln (10,11) gemäß ihrer Auslegung anzuströmen. FIG. 4 schematically shows an inner housing 9 and the inner housing hub 17 and the turbine inlet 20. The inner housing 9 and the hub 17 thereby form an annular space with a circumference in which the flow flows. The mixing housing 80a and 80b according to the invention is angled relative to the inner housing 9 shown here in the circumferential direction. As a result, the combustion exhaust gas stream 22 is better diverted. The angling of the mixing housings 80a, b improves the flow diversion in the inner housing 9, which leads to the avoidance of flow accumulation points in the inner housing 9 and on the hub 17. As a result, the wear of the components is reduced by oxidation and erosion. Furthermore, the combustion exhaust gas flow 22 is improved in the inner housing 9, which leads to a homogenization of the flow in the inner housing 9. This improves the flow of the turbine 5 and there is an improvement in the performance values. By means of the invention, it is now possible to flow to the individual turbine blades (10, 11) according to their design.

Claims (7)

Gasturbinenanordnung umfassend zumindest einem Brenner (13) und einer Brennkammer (3) zum Verbrennen von Brennstoff, einem Mischgehäuse (80a,b) sowie einem sich daran anschließenden Innengehäuse (9) und eine im wesentlichen in Bezug auf den zumindest einen Brenner (13) senkrecht angeordneten Turbine (5), wobei das durch das verbrennen des Brennstoffs entstehende Verbrennungsabgas durch das Mischgehäuse (80a,b) in das Innengehäuse (9) strömt, wobei das Innengehäuse (9) derart ausgestaltet ist, dass das Verbrennungsabgas im Innengehäuse (9) in Richtung Turbine (5) umgelenkt wird, dadurch gekennzeichnet, dass das Mischgehäuse (80a,b) gegenüber dem Innengehäuse (9) angewinkelt ist, so dass eine bessere Umlenkung des Verbrennungsabgases in Richtung Turbine (5) bewirkt ist.A gas turbine arrangement comprising at least one burner (13) and a combustion chamber (3) for burning fuel, a mixing housing (80a, b) and an adjoining inner housing (9) and one substantially perpendicular to the at least one burner (13) arranged turbine (5), wherein the combustion exhaust gas resulting from the combustion of the fuel flows through the mixing housing (80 a, b) in the inner housing (9), wherein the inner housing (9) is designed such that the combustion exhaust gas in the inner housing (9) in Direction of turbine (5) is deflected, characterized in that the mixing housing (80 a, b) is angled relative to the inner housing (9), so that a better deflection of the combustion exhaust gas in the direction of the turbine (5) is effected. Gasturbinenanordnung nach einem der vorhergehenden Ansprüche dadurch gekennzeichnet, dass eine Welle (12) umfasst ist, an der die Turbine (5) angeordnet ist und wobei das Innengehäuse (9) eine Innengehäusenabe (17) aufweist, welche im Wesentlichen parallel zur Welle (12) angeordnet ist.Gas turbine arrangement according to one of the preceding claims, characterized in that a shaft (12) is arranged on which the turbine (5) is arranged, and wherein the inner housing (9) has an inner housing hub (17) which is substantially parallel to the shaft (12). is arranged. Gasturbinenanordnung nach Anspruch 2 dadurch gekennzeichnet, dass die Innengehäusenabe (17) wenigstens näherungsweise zylindrisch ausgebildet ist.Gas turbine arrangement according to claim 2, characterized in that the inner housing hub (17) is at least approximately cylindrical. Gasturbinenanordnung nach einem der vorhergehenden Ansprüche dadurch gekennzeichnet, dass der Winkel zwischen Innengehäuse (9) und Mischgehäuse (80a,b) derart ausgebildet ist, dass Strömungsstaupunkte im Innengehäuse (9) und an der Innengehäusenabe (17) vermieden sind.Gas turbine arrangement according to one of the preceding claims, characterized in that the angle between the inner housing (9) and the mixing housing (80a, b) is designed such that Strömungsstaupunkte in the inner housing (9) and on the inner housing hub (17) are avoided. Gasturbine (5) umfassend zumindest zwei sich im Wesentlichen gegenüberliegende Brenner und Brennkammern sowie einem sich jeweils daran anschließenden Mischgehäuse (80 a) und (80b) und einem sich daran anschließenden Innengehäuse (9) sowie einer um eine Welle (12) angeordneten Innengehäusenabe (17) wobei durch das Innengehäuse (9) und die Innengehäusenabe (17) ein Ringraum mit einem Umfang ausgebildet wird dadurch gekennzeichnet, dass die Mischgehäuse (80a) und (80b) in Umfangsrichtung angewinkelt sind.Gas turbine (5) comprising at least two substantially oppositely disposed burner and combustion chambers and a respectively subsequent mixing housing (80 a) and (80 b) and an adjoining inner housing (9) and about a shaft (12) arranged inner housing hub (17 ), wherein by the inner housing (9) and the inner housing hub (17) an annular space is formed with a circumference, characterized in that the mixing housings (80 a) and (80 b) are angled in the circumferential direction. Verfahren zur Turbinenanströmung umfassend zumindest einem Brenner und einer Brennkammer, in welchem Brennstoff zu Verbrennungsabgasen verbrannt wird, und einem Mischgehäuse (80a,b) sowie ein sich daran anschließendes Innengehäuse (9) zum Führen der Verbrennungsabgase zu einer Turbine (5), die im wesentlichen senkrecht zur Strömungsrichtung der Verbrennungsabgase in der Brennkammer (3) angeordnet ist, wobei im Innengehäuse (9) die Verbrennungsabgase in Richtung Turbine (5) abgelenkt werden, dadurch gekennzeichnet, dass mittels anwinkeln des Mischgehäuses (80a,b) gegenüber dem Innengehäuse (9) die Strömungsumleitung im Innengehäuse (9) verbessert wird, so dass eine bessere Turbinenanströmung erzielt wird.A method of turbine induction comprising at least one burner and a combustion chamber in which fuel is combusted to combustion exhaust gases and a mixing housing (80a, b) and an adjoining inner housing (9) for guiding the combustion exhaust gases to a turbine (5) substantially is arranged perpendicular to the flow direction of the combustion exhaust gases in the combustion chamber (3), wherein in the inner housing (9) the combustion exhaust gases are deflected towards the turbine (5), characterized in that by means of angling the mixing housing (80a, b) relative to the inner housing (9) the flow diversion in the inner housing (9) is improved, so that a better Turbinenanströmung is achieved. Verfahren zur Turbinenanströmung dadurch gekennzeichnet, dass die einzelnen Turbinenschaufeln (10,11) gemäß ihrer Auslegung angeströmt werden.Method for Turbinenanströmung characterized in that the individual turbine blades (10,11) are flown according to their design.
EP08014874A 2008-08-21 2008-08-21 Gas turbine comprising angled duct and method for guiding the flow onto the turbine Withdrawn EP2157286A1 (en)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2526281A (en) * 1947-04-10 1950-10-17 Wright Aeronautical Corp Turbine and turbine nozzle construction
US3650106A (en) * 1968-10-18 1972-03-21 Bennes Marrel Sa Combustion chamber for gas turbine
EP0493004A1 (en) * 1990-12-20 1992-07-01 Honda Giken Kogyo Kabushiki Kaisha Gas generator for a gas turbine
EP1391583A1 (en) * 2002-08-23 2004-02-25 MAN Turbomaschinen AG Air cooled transition duct
DE10348447A1 (en) * 2003-10-17 2005-07-07 Siemens Ag Assembly and maintenance platform for a gas turbine esp. a stationary gas turbine with a walk in flame tube where the platform can be disassembled

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2526281A (en) * 1947-04-10 1950-10-17 Wright Aeronautical Corp Turbine and turbine nozzle construction
US3650106A (en) * 1968-10-18 1972-03-21 Bennes Marrel Sa Combustion chamber for gas turbine
EP0493004A1 (en) * 1990-12-20 1992-07-01 Honda Giken Kogyo Kabushiki Kaisha Gas generator for a gas turbine
EP1391583A1 (en) * 2002-08-23 2004-02-25 MAN Turbomaschinen AG Air cooled transition duct
DE10348447A1 (en) * 2003-10-17 2005-07-07 Siemens Ag Assembly and maintenance platform for a gas turbine esp. a stationary gas turbine with a walk in flame tube where the platform can be disassembled

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