EP2318664B1 - Gas turbine assembly with a non-cylindrical transition duct - Google Patents

Gas turbine assembly with a non-cylindrical transition duct Download PDF

Info

Publication number
EP2318664B1
EP2318664B1 EP09807919.7A EP09807919A EP2318664B1 EP 2318664 B1 EP2318664 B1 EP 2318664B1 EP 09807919 A EP09807919 A EP 09807919A EP 2318664 B1 EP2318664 B1 EP 2318664B1
Authority
EP
European Patent Office
Prior art keywords
inner casing
hub
turbine
inner housing
bosses
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.)
Not-in-force
Application number
EP09807919.7A
Other languages
German (de)
French (fr)
Other versions
EP2318664A1 (en
Inventor
Andre Botzen
Karl Klein
Marco Link
Oliver Lüsebrink
Nicolas Savilius
Oliver Schneider
Marc Tertilt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP09807919.7A priority Critical patent/EP2318664B1/en
Publication of EP2318664A1 publication Critical patent/EP2318664A1/en
Application granted granted Critical
Publication of EP2318664B1 publication Critical patent/EP2318664B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/43—Radial inlet and axial outlet
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular 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
    • F05D2250/30—Arrangement of components
    • F05D2250/33—Arrangement of components symmetrical
    • 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 perpendicularly with respect 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.
  • 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 exhaust 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 to the circulating space for turbine entry. This results in an inhomogeneous flow of the turbine 5. This is to be expected with performance losses.
  • the GB 2 361 302 A far an arcuate inner housing formed with an inner housing hub having ribs or furrows.
  • 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 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 with inner housing hub and a turbine arranged substantially perpendicular 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 by means of the inner housing hub 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.
  • the inner housing hub has at least two bosses, wherein the at least two bosses are arranged offset to an inner housing inlet, so that the incoming combustion exhaust gas stream in its entirety is deflected around the inner housing hub.
  • the at least two projections have approximately the shape of a lemon with the inner housing hub. This results in a homogenization of the hot gas flows of the exhaust gas or the Exhaust gas flow, whereby an improved turbine flow is achieved.
  • the humps can be variably designed with respect to their length in the A-axis direction.
  • the humps are preferably symmetrical with respect to a B-axis. Impacted exhaust gas is now better diverted by the aerodynamic shape of the inner housing hub.
  • the at least two projections are fastened by being attached to the inner housing hub. This can also be partial welding to the hub. Already manufactured hubs can be retrofitted with it. Furthermore, it is also possible to manufacture the at least two projections firmly on the inner housing hub. Preferably, the at least two projections are designed as a hollow body or as a solid body.
  • the at least two bosses are arranged opposite one another on the inner housing hub.
  • the exhaust gases are deflected symmetrically.
  • a gas turbine which comprises at least two essentially oppositely located burners and combustion chambers for combustion of fuel.
  • This can be especially known Silobrennschn.
  • the inner housing hub has at least two opposing humps. Due to this improved aerodynamic shape of the inner housing hub, the Verbrennüngsabgas is thus better redirected.
  • the exhaust gas flow coming from the mixing housing is essentially deflected or divided and deflected in its entirety in one direction. As a result, both a better deflection of the exhaust gas and an improved flow of the turbine is achieved.
  • the at least two humps are offset to an inner housing entry arranged so that the incoming combustion exhaust gas stream in its entirety is deflected around the inner housing hub.
  • the at least two projections have approximately the shape of a lemon with the inner housing hub. This results in a homogenization of the hot gas flows of the exhaust gas or the exhaust gas flow, whereby an improved turbine flow is achieved.
  • the individual turbine blades are flown according to their design. This improves the performance of the turbine.
  • 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 separation chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9.
  • the silo combustion chambers 3 are used for combustion a fuel, wherein the hot and high-pressure exhaust gases 2 are supplied via the mixing housing 8 and the inner housing 9 of the turbine 5 to drive them.
  • 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, that the combustion exhaust gases leads 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 via a common annulus. 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 to say the flows impinge on the hub 17 at the level of a parting line (not shown) and then distribute themselves on the surrounding space Turbine inlet. This results in an inhomogeneous flow to the turbine, which is expected to result in performance losses.
  • FIG. 4 schematically shows an inner housing 9 and the inner housing hub 170 according to the invention and the turbine inlet 20 of a gas turbine with Silobrennschn 3.
  • the inner housing hub 170 is provided with two bosses 23a, 23b in these embodiments.
  • the inner housing hub 170 thus essentially has the shape of a lemon.
  • the humps 23a, 23b are symmetrical to an axis of symmetry B.
  • Incoming exhaust gas streams 22a, 22b are now redirected by these humps 23a, 23b aerodynamically improved, so no longer bounce as in the inner housing hub 17 according to the prior art substantially perpendicular to the hub , This results in a homogenization of the hot gas flow in the inner housing, whereby the turbine is better flowed.
  • the turbine blades 10,11 can be flown according to their design. This results in improved performance values of the turbine 5.
  • flow accumulation points in the inner housing 9 and on the hub 170 are avoided.
  • the wear of the individual components is avoided by erosion and oxidation.
  • the humps are arranged offset to the inner housing inlet 25.
  • the incoming exhaust gas stream 22a (and 22b) is deflected substantially all around the inner housing hub 170.
  • it is gas turbines with two Silobrennsch 3. The number of
  • Humps 23a, 23b and the size of the humps 23a, 23b can therefore vary depending on the gas turbine type and design of the individual gas turbine.

Landscapes

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

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.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 perpendicularly with respect 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.

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 exhaust 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 to the circulating space for turbine entry. This results in an inhomogeneous flow of the turbine 5. This is to be expected with performance losses.

Die GB 2 361 302 A weit ein bogenförmig ausgebildetes Innengehäuse auf mit einer Innengehäusenabe, welche Rippen oder Furchen aufweist.The GB 2 361 302 A far an arcuate inner housing formed with an inner housing hub having ribs or furrows.

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.Compared to this prior art, it is an object of the present invention to provide an improved gas turbine assembly which has an improved gas turbine engine assembly Turbine flow ensured. Another task is the specification of such a gas turbine.

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 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 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 mit Innengehäusenabe 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 mittels der Innengehäusenabe 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. Hier greift nun die Erfindung ein, und löst dieses lang bestehende Problem, indem die Innengehäusenabe nichtzylindrisch ausgebildet ist, wodurch die Turbine besser angeströmt wird. Dadurch werden die Verbrennungsabgase besser umgelenkt und prallen im Wesentlichen nicht länger senkrecht auf die Innengehäusenabe auf. Dies ermöglicht es, die einzelnen Turbinenschaufeln gemäß ihrer Auslegung anzuströmen. Die Innengehäusenabe weist zumindest zwei Buckel auf, wobei die zumindest zwei Buckel versetzt zu einem Innengehäuseeintritt angeordnet sind, so dass der ankommende Verbrennungsabgasstrom in seiner Gesamtheit um die Innengehäusenabe herumgelenkt wird. Die zumindest zwei Buckel weisen mit der Innengehäusenabe näherungsweise die Form einer Zitrone auf. Daraus resultiert eine Vergleichmäßigung der Heißgasströme des Abgases bzw. der Abgasströmung, wodurch eine verbesserte Turbinenanströmung erzielt wird.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 with inner housing hub and a turbine arranged substantially perpendicular 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 by means of the inner housing hub 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. Here, the invention intervenes, and solves this long-standing problem by the Innengehäusenabe is non-cylindrical, whereby the turbine is better flowed. As a result, the combustion exhaust gases are better deflected and substantially no longer bounce perpendicular to the inner housing hub. This makes it possible to feed the individual turbine blades according to their design. The inner housing hub has at least two bosses, wherein the at least two bosses are arranged offset to an inner housing inlet, so that the incoming combustion exhaust gas stream in its entirety is deflected around the inner housing hub. The at least two projections have approximately the shape of a lemon with the inner housing hub. This results in a homogenization of the hot gas flows of the exhaust gas or the Exhaust gas flow, whereby an improved turbine flow is achieved.

Die Buckel sind je nach Brennkammer- und Mischgehäuseauslegung bzgl. ihrer Länge in der A-Achsen Richtung variabel auslegbar. Die Buckel sind vorzugsweise symmetrisch bezüglich einer B-Achse. Aufprallendes Abgas wird nun durch die aerodynamische Form der Innengehäusenabe besser umgeleitet.Depending on the design of the combustion chamber and mixing housing, the humps can be variably designed with respect to their length in the A-axis direction. The humps are preferably symmetrical with respect to a B-axis. Impacted exhaust gas is now better diverted by the aerodynamic shape of the inner housing hub.

Dabei sind die zumindest zwei Buckel durch Aufstecken an der Innengehäusenabe befestigt. Dies kann auch teilweises anschweißen an die Nabe sein. Bereits gefertigte Naben können damit auch nachgerüstet werden. Weiterhin ist es auch möglich, die zumindest zwei Buckel fest an der Innengehäusenabe mit zu fertigen. Bevorzugt sind die zumindest zwei Buckel als ein Hohlkörper oder als ein Massivkörper ausgeführt.In this case, the at least two projections are fastened by being attached to the inner housing hub. This can also be partial welding to the hub. Already manufactured hubs can be retrofitted with it. Furthermore, it is also possible to manufacture the at least two projections firmly on the inner housing hub. Preferably, the at least two projections are designed as a hollow body or as a solid body.

Bevorzugt sind die mindestens zwei Buckel sich gegenüberliegend an der Innengehäusenabe angeordnet. Dadurch werden die Abgase symmetrisch abgelenkt.Preferably, the at least two bosses are arranged opposite one another on the inner housing hub. As a result, the exhaust gases are deflected symmetrically.

Erfindungsgemäß wird weiterhin eine Gasturbine offenbart, welche zumindest zwei sich im Wesentlichen gegenüberliegende Brenner und Brennkammern zur Verbrennung von Brennstoff, umfasst. Dies können vor allem bekannte Silobrennkammern sein. An diese schließen sich jeweils die Mischgehäuse sowie ein Innengehäuse mit einer um eine Welle angeordneten Innengehäusenabe an. Die Innengehäusenabe weist mindestens zwei sich gegenüberliegende Buckel auf. Durch diese verbesserte aerodynamische Form der Innengehäusenabe wird das Verbrennüngsabgas somit besser umgeleitet. Je nach Anordnung der Buckel auf der Innengehäusenabe wird der vom Mischgehäuse kommende Abgasstrom im Wesentlichen in seiner Gesamtheit in eine Richtung umgelenkt oder geteilt und umgelenkt. Dadurch wird sowohl eine bessere Umlenkung des Abgases als auch eine verbesserte Anströmung der Turbine erzielt. Die zumindest zwei Buckel sind versetzt zu einem Innengehäuseeintritt angeordnet, so dass der ankommende Verbrennungsabgasstrom in seiner Gesamtheit um die Innengehäusenabe herumgelenkt wird. Die zumindest zwei Buckel weisen mit der Innengehäusenabe näherungsweise die Form einer Zitrone auf. Daraus resultiert eine Vergleichmäßigung der Heißgasströme des Abgases bzw. der Abgasströmung, wodurch eine verbesserte Turbinenanströmung erzielt wird.According to the invention, furthermore, a gas turbine is disclosed, which comprises at least two essentially oppositely located burners and combustion chambers for combustion of fuel. This can be especially known Silobrennkammern. These are followed by the mixing housing and an inner housing with an inner housing hub arranged around a shaft. The inner housing hub has at least two opposing humps. Due to this improved aerodynamic shape of the inner housing hub, the Verbrennüngsabgas is thus better redirected. Depending on the arrangement of the projections on the inner housing hub, the exhaust gas flow coming from the mixing housing is essentially deflected or divided and deflected in its entirety in one direction. As a result, both a better deflection of the exhaust gas and an improved flow of the turbine is achieved. The at least two humps are offset to an inner housing entry arranged so that the incoming combustion exhaust gas stream in its entirety is deflected around the inner housing hub. The at least two projections have approximately the shape of a lemon with the inner housing hub. This results in a homogenization of the hot gas flows of the exhaust gas or the exhaust gas flow, whereby an improved turbine flow is achieved.

Bevorzugt werden die einzelnen Turbinenschaufeln gemäß ihrer Auslegung angeströmt. Dadurch verbessern sich die Performancewerte der Turbine.Preferably, the individual turbine blades are flown according to their design. This improves the performance of the turbine.

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 ein Ausführungsbeispiel der erfindungsgemäßen Innengehäusenabe mit zwei Buckeln.
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 an embodiment of the invention Innengehäusenabe with two humps.

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 separation chambers 3, a turbine 5, a compressor 7, two mixing housings 8 and an inner housing 9. The silo combustion chambers 3 are used for combustion a fuel, wherein the hot and high-pressure exhaust gases 2 are supplied via the mixing housing 8 and the inner housing 9 of the turbine 5 to drive them.

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, dass 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, that the combustion exhaust gases leads 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 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. Dadurch ergibt sich eine inhomogene Anströmung auf die Turbine, 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 via a common annulus. 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 to say the flows impinge on the hub 17 at the level of a parting line (not shown) and then distribute themselves on the surrounding space Turbine inlet. This results in an inhomogeneous flow to the turbine, which is expected to result in performance losses.

FIG 4 zeigt schematisch ein Innengehäuse 9 sowie die erfindungsgemäße Innengehäusenabe 170 und den Turbineneintritt 20 einer Gasturbine mit Silobrennkammern 3. Um eine gut optimierte Anströmung auf die Turbine 5 zu erreichen, muss der Abgasstrom aus beiden Mischgehäusen 8a,8b eine definierte Führung vom Eintritt am Innengehäuse 9 bis zum Turbineneintritt 20 erfahren. Die Innengehäusenabe 170 ist in diesen Ausführungsbeispielen mit zwei Buckeln 23a,23b versehen. Die Innengehäusenabe 170 weist somit im wesentlich die Form einer Zitrone auf. Die Buckel 23a,23b sind symmetrisch zu einer Symmetrieachse B. Ankommende Abgasströme 22a,22b werden durch diese Buckel 23a,23b nun aerodynamisch verbessert umgeleitet, prallen also nicht mehr wie in der Innengehäusenabe 17 nach dem Stand der Technik im wesentlichen senkrecht auf die Nabe auf. Daraus resultiert eine Vergleichmäßigung der Heißgasströmung im Innengehäuse, wodurch die Turbine besser angeströmt wird. Die Turbineschaufeln 10,11 können so gemäß ihrer Auslegung angeströmt werden. Dadurch ergeben sich verbesserte Performancewerte der Turbine 5. Weiterhin werden Strömungsstaupunkten im Innengehäuse 9 und an der Nabe 170 vermieden. Dadurch wird der Verschleiß der einzelnen Komponenten durch Erosion und Oxidation vermieden. Im Ausführungsbeispiel FIG 4 sind die Buckel versetzt zum Innengehäuseeintritt 25 angeordnet. In diesem Fall wird der ankommende Abgasstrom 22a (und 22b) im Wesentlichen in seiner Gesamtheit um die Innengehäusenabe 170 herum abgelenkt. In dem Beispiel handelt es sich um Gasturbinen mit zwei Silobrennkammern 3. Die Anzahl der FIG. 4 schematically shows an inner housing 9 and the inner housing hub 170 according to the invention and the turbine inlet 20 of a gas turbine with Silobrennkammern 3. In order to achieve a well optimized flow to the turbine 5, the exhaust gas flow from both mixing housings 8a, 8b a defined guide from the inlet to the inner housing 9 learn about the turbine entry 20. The inner housing hub 170 is provided with two bosses 23a, 23b in these embodiments. The inner housing hub 170 thus essentially has the shape of a lemon. The humps 23a, 23b are symmetrical to an axis of symmetry B. Incoming exhaust gas streams 22a, 22b are now redirected by these humps 23a, 23b aerodynamically improved, so no longer bounce as in the inner housing hub 17 according to the prior art substantially perpendicular to the hub , This results in a homogenization of the hot gas flow in the inner housing, whereby the turbine is better flowed. The turbine blades 10,11 can be flown according to their design. This results in improved performance values of the turbine 5. Furthermore, flow accumulation points in the inner housing 9 and on the hub 170 are avoided. As a result, the wear of the individual components is avoided by erosion and oxidation. In the embodiment FIG. 4 the humps are arranged offset to the inner housing inlet 25. In this case, the incoming exhaust gas stream 22a (and 22b) is deflected substantially all around the inner housing hub 170. In the example, it is gas turbines with two Silobrennkammern 3. The number of

Buckel 23a,23b sowie die Größe der Buckel 23a,23b können daher je nach Gasturbinentyp und Ausgestaltung der einzelnen Gasturbine variieren.Humps 23a, 23b and the size of the humps 23a, 23b can therefore vary depending on the gas turbine type and design of the individual gas turbine.

Claims (6)

  1. Gas turbine arrangement comprising at least one burner (13) and a combustion chamber (3) for burning fuel, a mixing casing (8a,b) and, adjoining this, an inner casing (9) with an inner casing hub (170) and a turbine (5) arranged essentially perpendicular with respect to the at least one burner (13), wherein the combustion exhaust gas (22a, 22b) resulting from the combustion of the fuel flows through the mixing casing (8a,b) into the inner casing (9), wherein the inner casing (9) is configured such that, in the inner casing (9), the combustion exhaust gas (22a, 22b) is deflected in the direction of the turbine (5) by means of the inner casing hub (170), wherein
    the inner casing hub (170) has at least two bosses (23a), (23b), wherein the at least two bosses (23a), (23b) are arranged offset with respect to an inner casing inlet (25) such that all of the incident combustion exhaust gas stream (22a, 22b) is deflected around the inner casing hub (170), characterized in that the at least two bosses (23a), (23b) have, with the inner casing hub (170), approximately the shape of a lemon.
  2. Gas turbine arrangement according to Claim 1, characterized in that the at least two bosses (23a), (23b) are attached by fitting onto the inner casing hub (170).
  3. Gas turbine arrangement according to Claim 1, characterized in that the at least two bosses (23a), (23b) are produced solidly on the inner casing hub (170).
  4. Gas turbine arrangement according to one of the preceding claims,
    characterized in that the at least two bosses (23a), (23b) are embodied as a hollow body or as a solid body.
  5. Gas turbine arrangement according to one of the preceding claims,
    characterized in that the at least two bosses (23a), (23b) are arranged opposite one another on the inner casing hub (170).
  6. Gas turbine (5) comprising at least two burners (13) essentially opposite one another and combustion chambers (3) for burning fuel and, adjoining each of these, a mixing casing (8a), (8b) and, adjoining this, an inner casing (9) and an inner casing hub (170) arranged around a shaft (12), wherein
    the inner casing hub (170) has at least two bosses (23a), (23b) opposite one another, wherein the bosses (23a, 23b) are arranged offset with respect to an inner casing inlet (25) such that all of the incident combustion exhaust gas stream (22a, 22b) from the combustion chambers (3) is deflected around the inner casing hub (170),
    characterized in that the at least two bosses (23a), (23b) have, with the inner casing hub (170), approximately the shape of a lemon.
EP09807919.7A 2008-08-21 2009-07-16 Gas turbine assembly with a non-cylindrical transition duct Not-in-force EP2318664B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09807919.7A EP2318664B1 (en) 2008-08-21 2009-07-16 Gas turbine assembly with a non-cylindrical transition duct

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08014872A EP2157284A1 (en) 2008-08-21 2008-08-21 Gas turbine assembly with a non-cylindrical transition duct and method for guiding the flow onto the turbine
PCT/EP2009/059126 WO2010020487A1 (en) 2008-08-21 2009-07-16 Gas turbine arrangement having a non-cylindrical inner housing hub, and method for directing flow to a turbine
EP09807919.7A EP2318664B1 (en) 2008-08-21 2009-07-16 Gas turbine assembly with a non-cylindrical transition duct

Publications (2)

Publication Number Publication Date
EP2318664A1 EP2318664A1 (en) 2011-05-11
EP2318664B1 true EP2318664B1 (en) 2016-05-04

Family

ID=40849151

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08014872A Withdrawn EP2157284A1 (en) 2008-08-21 2008-08-21 Gas turbine assembly with a non-cylindrical transition duct and method for guiding the flow onto the turbine
EP09807919.7A Not-in-force EP2318664B1 (en) 2008-08-21 2009-07-16 Gas turbine assembly with a non-cylindrical transition duct

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08014872A Withdrawn EP2157284A1 (en) 2008-08-21 2008-08-21 Gas turbine assembly with a non-cylindrical transition duct and method for guiding the flow onto the turbine

Country Status (2)

Country Link
EP (2) EP2157284A1 (en)
WO (1) WO2010020487A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015207760A1 (en) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Hot gas carrying housing

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3117515C2 (en) * 1980-05-07 1983-11-10 Brown, Boveri & Cie Ag, 6800 Mannheim Overflow housing
GB2293232B (en) * 1994-09-15 1998-05-20 Rolls Royce Plc A combustion chamber assembly
GB2361302A (en) * 2000-04-13 2001-10-17 Rolls Royce Plc Discharge nozzle for a gas turbine engine combustion chamber

Also Published As

Publication number Publication date
EP2318664A1 (en) 2011-05-11
EP2157284A1 (en) 2010-02-24
WO2010020487A1 (en) 2010-02-25

Similar Documents

Publication Publication Date Title
DE4242494C1 (en) Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages
DE60019264T2 (en) EXHAUST MIXING DEVICE AND DEVICE WITH SUCH A DEVICE
EP2167793B1 (en) Exhaust gas turbocharger for an internal combustion engine
DE4309636C2 (en) Radially flow-through turbocharger turbine
EP2179143B1 (en) Gap cooling between combustion chamber wall and turbine wall of a gas turbine installation
DE2031612A1 (en) Multi-stage axial compressor with an air discharge system as an intermediate stage
EP0834646A1 (en) Containment device for the radial turbine of a turbocharger
EP2379846B1 (en) Guide vane support system for a turbomachine
EP1706597A1 (en) Gas turbine with axially displaceable rotor
EP3064706A1 (en) Guide blade assembly for a flow engine with axial flow
DE2454054A1 (en) INTERNAL POWER PLANT AND GAS GENERATOR FOR GAS TURBINE ENGINES
EP2617947B1 (en) Aircraft gas turbine engine with adjustable fan
EP1532368B1 (en) Compressor in an exhaust-gas turbocharger for an internal combustion engine
EP0806547B1 (en) Axial turbine for turbochargers
DE19839592A1 (en) Fluid machine with cooled rotor shaft
EP0532907B1 (en) Axial turbine
DE102019125654A1 (en) TURBINE SHOVEL
EP2526263A2 (en) Housing system for an axial turbomachine
EP2318664B1 (en) Gas turbine assembly with a non-cylindrical transition duct
DE102010044819B4 (en) Axial flow turbine and method of removing flow from an axial flow turbine
WO2011128179A1 (en) Swirl generator for a torch
EP3298285B1 (en) Guide vane for a bladed diffuser of a centrifugal compressor
DE1258360B (en) Spiral casing for flow machines, especially turbines, pumps or pump turbines
EP1632650B1 (en) Steam turbine
DE2930184A1 (en) OVERLOAD DEVICE OF A MULTI-HOUSED TURBINE

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20110128

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20120831

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20151130

RIN1 Information on inventor provided before grant (corrected)

Inventor name: BOTZEN, ANDRE

Inventor name: SAVILIUS, NICOLAS

Inventor name: TERTILT, MARC

Inventor name: SCHNEIDER, OLIVER

Inventor name: LINK, MARCO

Inventor name: LUESEBRINK, OLIVER

Inventor name: KLEIN, KARL

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 797100

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502009012544

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160504

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160804

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160905

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160805

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009012544

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

26N No opposition filed

Effective date: 20170207

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160804

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170201

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160801

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160731

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160731

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170331

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160804

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160716

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160716

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 797100

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160716

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160716

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090716

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160504