EP2318664A1 - Gas turbine arrangement having a non-cylindrical inner housing hub, and method for directing flow to a turbine - Google Patents

Gas turbine arrangement having a non-cylindrical inner housing hub, and method for directing flow to a turbine

Info

Publication number
EP2318664A1
EP2318664A1 EP09807919A EP09807919A EP2318664A1 EP 2318664 A1 EP2318664 A1 EP 2318664A1 EP 09807919 A EP09807919 A EP 09807919A EP 09807919 A EP09807919 A EP 09807919A EP 2318664 A1 EP2318664 A1 EP 2318664A1
Authority
EP
European Patent Office
Prior art keywords
inner housing
turbine
gas turbine
hub
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.)
Granted
Application number
EP09807919A
Other languages
German (de)
French (fr)
Other versions
EP2318664B1 (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

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 and a method for Turbinenanströmung.
  • a gas turbine installation 1 essentially comprises one or more combustion chambers 3 with burners 13 (see FIG. 2) in which a fuel is burnt, a turbine 5 which extracts the hot and pressurized combustion exhaust gases from the combustion chambers 3 be fed 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 on the sucked in the necessary air for combustion and compressed to a higher pressure.
  • FIG. 1 shows such a gas turbine plant in a schematic view, wherein FIGl shows a horizontal section through the system.
  • 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.
  • Gas turbine plant 1 then flow the combustion exhaust gases substantially parallel to the axis of rotation A of the turbine shaft 12th
  • Inner housing 9 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.
  • Another object of the present invention is 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.
  • 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 9.
  • the object related to the method is solved by claim 10.
  • 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 resulting from the combustion of the fuel flows through the mixing housing into the inner housing, wherein the inner housing is configured such that the combustion exhaust gas in the inner housing by means of
  • Inner housing hub is deflected towards 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 réellegeophusenabe 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 one projection. Depending on the design of the combustion chamber and mixing housing, this projection is variable in terms of its length in the A-axis direction.
  • the hump is preferably symmetrical with respect to a B-axis.
  • the at least one projection is attached 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 that at least one hump firmly on the
  • the at least one projection is designed as a hollow body or as a solid body.
  • At least two humps are present. This is particularly advantageous when the combustion chambers are so-called silo combustion chambers.
  • the at least two bosses are arranged opposite one another on the inner housing hub.
  • the exhaust gases are deflected symmetrically.
  • the at least two projections with the inner housing hub approximately the shape of a lemon. 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.
  • 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 combustion exhaust gas is thus better diverted. Indeed, once the humps are located on the inner shell hub, the exhaust stream coming from the mixing shell is substantially diverted or split and deflected in its entirety. As a result, both a better deflection of the exhaust gas and an improved flow of the turbine is achieved.
  • a method for turbine flow is 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 arranged substantially perpendicular to the flow direction of the combustion exhaust gases in the combustion chamber, wherein in the inner housing by means of a mecanicgephaseusenabe the combustion exhaust gases are deflected toward the turbine, wherein by applying at least one projection on the mecanicalenabe improves the flow diversion of the combustion exhaust gas flow in the inner housing so that a better turbine flow is achieved.
  • the individual turbine blades are flown according to their design. This improves the performance of the turbine.
  • Silo combustion chamber, the mixing housing and the inner housing according to the prior art, 3 shows a detail of an inner housing and associated inner housing hub according to the prior art
  • FIG 5 shows schematically a further embodiment of the inner housing hub according to the invention with two bosses.
  • FIG. 1 An example of gas turbine plant 1 is shown in FIG. 1 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 to burn 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 upper end 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 surrounded by 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 and FIG. 5 schematically show an inner housing 9 and the inner housing hub 170 and the turbine inlet 20 of a gas turbine with silo combustion chambers 3.
  • the exhaust gas flow from both mixing housings 8a, 8b has to have a defined guidance from Admission to the inner housing 9 to the turbine inlet 20 experienced.
  • 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 aerodynamically improved by these humps 23a, 23b deflected, 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. As a result, the wear of the individual components is avoided by erosion and oxidation.
  • the bosses 23a, 23b can be arranged directly opposite the inner housing inlet 25, which represents the transition from the mixed housing 8a, 8b and inner housing 9.
  • the incoming exhaust gas stream 22a, 22b is divided into two parts and the resulting streams are then distributed around the inner housing hub 170.
  • the projections are offset from the inner housing inlet 25.

Landscapes

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

Abstract

The invention relates to a gas turbine arrangement, comprising at least one burner (13) and one combustion chamber (3) for burning fuel, a mixing housing (8a, b), an inner housing (9) connected thereto comprising an inner housing hub (170), and a turbine (5) arranged substantially perpendicular relative to the at least one burner (13), wherein the combustion exhaust gas produced by the combustion of the fuel flows through the mixing housing (8a, b) into the inner housing (9), wherein the inner housing (9) is designed in such a way that the combustion exhaust gas in the inner housing (9) is redirected in the direction of the turbine (5) by means of the inner housing hub (170), wherein the inner housing hub (170) is designed non-cylindrically. The invention further relates to a gas turbine and a method for improved directing of flow to a turbine.

Description

Beschreibung description
GASTURBINENANORDNUNG MIT NICHTZYLINDRISCHER INNENGEHÄUSENABE UND VERFAHREN ZUR TURBINENANSTRÖMUNGGAS TURBINE ARRANGEMENT WITH NON-CYLINDRICAL INTERNAL CABINET AND METHOD OF TURBINE TURNING
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 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 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 installation 1 (see FIG. 1) essentially comprises one or more combustion chambers 3 with burners 13 (see FIG. 2) in which a fuel is burnt, a turbine 5 which extracts the hot and pressurized combustion exhaust gases from the combustion chambers 3 be fed 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 on the sucked in the necessary air for combustion 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. FIG 1 zeigt eine derartige Gasturbinenanlage in einer schematischen Ansicht, wobei FIGl einen horizontalen Schnitt durch die Anlage zeigt.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. 1 shows such a gas turbine plant in a schematic view, wherein FIGl shows a horizontal section through the system.
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 derFrom 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, when entering the turbine 5 of
Gasturbinenanlage 1 strömen die Verbrennungsabgase dann im Wesentlichen parallel zur Rotationsachse A der Turbinenwelle 12.Gas turbine plant 1 then flow the combustion exhaust gases substantially parallel to the axis of rotation A of the turbine shaft 12th
Beim Zuführen des Gases zur Turbine 5 wird das Gas imWhen supplying the gas to the turbine 5, the gas is in
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.Inner housing 9 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.
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. 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 9 gelöst. Die auf das Verfahren bezogene Aufgabe wird durch Anspruch 10 gelöst. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.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. 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 9. The object related to the method is solved by claim 10. 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 derA 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 resulting from the combustion of the fuel flows through the mixing housing into the inner housing, wherein the inner housing is configured such that the combustion exhaust gas in the inner housing by means of
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 .Inner housing hub is deflected towards 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.
In bevorzugter Ausgestaltung weist die Innengehäusenabe zumindest einen Buckel auf. Dieser Buckel ist je nach Brennkammer- und Mischgehäuseauslegung bzgl. seiner Länge in der A -Achsen Richtung variable auslegbar. Der Buckel ist vorzugsweise symmetrisch bezüglich einer B-Achse.In a preferred embodiment, the inner housing hub has at least one projection. Depending on the design of the combustion chamber and mixing housing, this projection is variable in terms of its length in the A-axis direction. The hump is preferably symmetrical with respect to a B-axis.
Aufprallendes Abgas wird nun durch die aerodynamische Form der Innengehäusenabe besser umgeleitet. Dabei ist der zumindest eine 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, den zumindest einen Buckel fest an derImpacted exhaust gas is now better diverted by the aerodynamic shape of the inner housing hub. In this case, the at least one projection is attached 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 that at least one hump firmly on the
Innengehäusenabe mit zu fertigen. Bevorzugt ist der zumindest eine Buckel als ein Hohlkörper oder als ein Massivkörper ausgeführt .Inner housing hub with to manufacture. Preferably, the at least one projection is designed as a hollow body or as a solid body.
In bevorzugte Ausgestaltung sind mindestens zwei Buckel vorhanden. Dies ist besonders dann vorteilhaft, wenn es sich bei den Brennkammern um sogenannte Silobrennkammern handelt. Bevorzugt sind die mindestens zwei Buckel sich gegenüberliegend an der Innengehäusenabe angeordnet. Dadurch werden die Abgase symmetrisch abgelenkt. In bevorzugte Ausgestaltung weisen die mindestens zwei Buckel mit der Innengehäusenabe näherungeweise die Form einer Zitrone auf. Daraus resultiert eine Vergleichmäßigung der Heißgasströme des Abgases bzw. der Abgasströmung, wodurch eine verbesserte Turbinenanströmung erzielt wird.In preferred embodiment, at least two humps are present. This is particularly advantageous when the combustion chambers are so-called silo combustion chambers. 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. In a preferred embodiment, the at least two projections with the inner housing hub approximately the shape of a lemon. 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.
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 a und b 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 Verbrennungsabgas somit besser umgeleitet. Ja 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. Erfindungsgemäß wird weiterhin ein Verfahren zur Turbinenanströmung offenbart, welches einen Brenner und eine Brennkammer, in welcher Brennstoff zu Verbrennungsabgasen verbrannt wird, umfasst, und ein Mischgehäuse sowie ein sich daran anschließendes Innengehäuse zum Führen derAccording 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 in each case by the mixing housing a and b 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 combustion exhaust gas is thus better diverted. Indeed, once the humps are located on the inner shell hub, the exhaust stream coming from the mixing shell is substantially diverted or split and deflected in its entirety. As a result, both a better deflection of the exhaust gas and an improved flow of the turbine is achieved. According to the invention, a method for turbine flow is 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
Verbrennungsabgase zu einer Turbine, die im wesentlichen senkrecht zur Strömungsrichtung der Verbrennungsabgase in der Brennkammer angeordnet ist, wobei im Innengehäuse mittels einer Innengehäusenabe die Verbrennungsabgase in Richtung Turbine abgelenkt werden, wobei mittels des Aufbringens mindestens eines Buckels an der Innengehäusenabe die Strömungsumleitung des Verbrennungsabgasstroms im Innengehäuse verbessert wird, so dass eine bessere Turbinenanströmung erzielt wird. Durch die aerodynamische Form der Nabe und der damit verbesserten Strömungsumleitung im Innengehäuse werden Strömungsstaupunkte im Innengehäuse und an der Innengehäusenabe vermieden. Dadurch wird der Verschleiß dieser Bauteile durch Oxidation und Erosion vermieden .Combustion exhaust gases to a turbine, which is arranged substantially perpendicular to the flow direction of the combustion exhaust gases in the combustion chamber, wherein in the inner housing by means of a Innengehäusenabe the combustion exhaust gases are deflected toward the turbine, wherein by applying at least one projection on the Innengehäusenabe improves the flow diversion of the combustion exhaust gas flow in the inner housing so that a better turbine flow is achieved. Due to the aerodynamic shape of the hub and thus improved flow diversion in the inner housing Strömungsstaupunkte be avoided in the inner housing and on the inner housing hub. This avoids the wear of these components due to oxidation and erosion.
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 .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 zeigt einen horizontalen Schnitt durch eine1 shows a horizontal section through a
Gasturbinenanlage mit zwei Silobrennkammern in einer stark schematisierten Darstellung nach dem Stand der Technik,Gas turbine plant with two silo combustion chambers in a highly schematized representation according to the prior art,
FIG 2 zeigt einen vertikalen Schnitt einer2 shows a vertical section of a
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,Silo combustion chamber, the mixing housing and the inner housing according to the prior art, 3 shows a detail of an inner housing and associated inner housing hub according to the prior art,
FIG 4 zeigt schematisch die erfindungsgemäße4 shows schematically the inventive
Innengehäusenabe mit zwei Buckeln,Inner housing hub with two humps,
FIG 5 zeigt schematisch ein weiteres Ausführungsbeispiel der erfindungsgemäßen Innengehäusenabe mit zwei Buckeln .5 shows schematically a further embodiment of the inner housing hub according to the invention with two bosses.
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 shown in FIG. 1 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 to burn 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, dass die Verbrennungsabgase zu dem Innengehäuse 9 führt.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 upper end 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 surrounded by 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 die3 shows the inner housing with inner housing hub 17 (vertical section through the inner housing), in which the
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.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 und FIG 5 zeigen 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. Die Buckel 23a, 23b können direkt gegenüber der Innengehäuseeintritt 25 angeordnet sein, welcher den Übergang von Mischgehäuse 8a, 8b und Innengehäuse 9 darstellt. In diesem Fall wird der ankommende Abgasstrom 22a, 22b zweigeteilt und die daraus entstehenden Ströme verteilen sich anschließend um die Innengehäusenabe 170. Im Ausführungsbeispiel FIG 5 sind die Buckel versetzt zum Innengehäuseeintritt 25 angeordnet. In diesem Fall wird der ankommende Abgasstrom 22a (und 22b) imFIG. 4 and FIG. 5 schematically show an inner housing 9 and the inner housing hub 170 and the turbine inlet 20 of a gas turbine with silo combustion chambers 3. In order to achieve a well-optimized flow to the turbine 5, the exhaust gas flow from both mixing housings 8a, 8b has to have a defined guidance from Admission to the inner housing 9 to the turbine inlet 20 experienced. 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 aerodynamically improved by these humps 23a, 23b deflected, 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. The bosses 23a, 23b can be arranged directly opposite the inner housing inlet 25, which represents the transition from the mixed housing 8a, 8b and inner housing 9. In this case, the incoming exhaust gas stream 22a, 22b is divided into two parts and the resulting streams are then distributed around the inner housing hub 170. In the exemplary embodiment, FIG. 5, the projections are offset from the inner housing inlet 25. In this case, the incoming exhaust gas stream 22a (and 22b) in
Wesentlichen in seiner Gesamtheit um die Innengehäusenabe 170 herum abgelenkt. In beiden Beispielen handelt es sich um Gasturbinen mit zwei Silobrennkammern 3. Die Anzahl der Buckel 23a, 23b sowie die Größe der Buckel 23a, 23b können daher je nach Gasturbinentyp und Ausgestaltung der einzelnen Gasturbine variieren. Essentially deflected in its entirety around the inner housing hub 170 around. Both examples are gas turbines with two silo combustion chambers 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.

Claims

Patentansprüche claims
1. Gasturbinenanordnung umfassend zumindest einem Brenner1. Gas turbine arrangement comprising at least one burner
(13) und einer Brennkammer (3) zum Verbrennen von Brennstoff, einem Mischgehäuse (8a, b) sowie einem sich daran anschließenden Innengehäuse (9) mit Innengehäusenabe (170) 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 (22a, 22b) durch das Mischgehäuse (8a, b) in das Innengehäuse (9) strömt, wobei das Innengehäuse (9) derart ausgestaltet ist, dass das Verbrennungsabgas (22a, 22b) im Innengehäuse (9) mittels der Innengehäusenabe (170) in Richtung Turbine (5) umgelenkt wird, d a d u r c h g e k e n n z e i c h n e t, d a s s das die Innengehäusenabe (170) nichtzylindrisch ausgebildet ist.(13) and a combustion chamber (3) for burning fuel, a mixing housing (8a, b) and an adjoining inner housing (9) with Innengehäusenabe (170) and one substantially with respect to the at least one burner (13) perpendicular arranged turbine (5), wherein the combustion exhaust gas produced by the burning of the fuel (22a, 22b) through the mixing housing (8a, b) in the inner housing (9) flows, wherein the inner housing (9) is designed such that the combustion exhaust gas ( 22a, 22b) in the inner housing (9) by means of the inner housing hub (170) in the direction of turbine (5) is deflected, characterized in that the inner housing hub (170) is non-cylindrical.
2. Gasturbinenanordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, d a s s die Innengehäusenabe (170) zumindest einen Buckel (23a, 23b) aufweist .2. A gas turbine engine as claimed in any one of the preceding claims, wherein the inner housing hub (170) has at least one boss (23a, 23b).
3. Gasturbinenanordnung nach einem der vorhergehenden3. Gas turbine arrangement according to one of the preceding
Ansprüche, d a d u r c h g e k e n n z e i c h n e t, d a s s der zumindest eine Buckel (23a, 23b) durch Aufstecken an derClaims, at least one projection (23a, 23b) by attaching to the at
Innengehäusenabe (170) befestigt ist.Inner housing hub (170) is attached.
4. Gasturbinenanordnung nach einem der Ansprüche 1-2, d a d u r c h g e k e n n z e i c h n e t, d a s s der zumindest eine Buckel (23a, 23b) fest an der4. The gas turbine arrangement according to claim 1, wherein the at least one projection (23a, 23b) is fixedly attached to the gas turbine assembly
Innengehäusenabe (170) gefertigt ist. Inner housing hub (170) is made.
5. Gasturbinenanordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, d a s s der zumindest eine Buckel (23a, 23b) als ein Hohlkörper oder als ein Massivkörper ausgeführt ist.5. Gas turbine arrangement according to one of the preceding claims, characterized in that at least one projection (23a, 23b) is designed as a hollow body or as a solid body.
6. Gasturbinenanordnung nach einem der vorhergehenden Ansprüche d a d u r c h g e k e n n z e i c h n e t, d a s s mindestens zwei Buckel (23a) , (23b) vorhanden sind.6. Gas turbine arrangement according to one of the preceding claims, in which at least two projections (23a), (23b) are present.
7. Gasturbinenanordnung nach Anspruch β d a d u r c h g e k e n n z e i c h n e t, d a s s mindestens zwei7. Gas turbine arrangement according to claim β d a d u r c h e c e n e c e s, at least two d
Buckel (23a) , (23b) versetzt zum Innengehäuseeintritt (25) angeordnet sind, so dass der ankommende Verbrennungsabgastrom in seiner Gesamtheit um die Innengehäusenabe (170) herumgelenkt wird.Humps (23a), (23b) are staggered to the inner housing inlet (25) so that the incoming combustion exhaust gas is directed in its entirety around the inner housing hub (170).
8. Gasturbinenanordnung einem der Ansprüche 6-8, d a d u r c h g e k e n n z e i c h n e t, d a s s die mindestens zwei Buckel (23a) , (23b) sich gegenüberliegend an der Innengehäusenabe (170) angeordnet sind.8. The gas turbine assembly of any one of claims 6-8, wherein said at least two bosses (23a), (23b) are disposed opposite one another on said inner housing hub (170).
9. Gasturbinenanordnung nach einem der Ansprüche 6-8, d a d u r c h g e k e n n z e i c h n e t, d a s s die mindestens zwei Buckel (23a) , (23b) mit der9. The gas turbine arrangement according to claim 6, wherein the at least two projections (23a), (23b) are connected to the gas turbine arrangement according to one of claims 6 to 8
Innengehäusenabe (170) näherungsweise die Form einer Zitrone aufweisen.Inner housing hub (170) have approximately the shape of a lemon.
10. Gasturbine (5) umfassend zumindest zwei sich im Wesentlichen gegenüberliegende Brenner (13) und10. Gas turbine (5) comprising at least two substantially opposite burner (13) and
Brennkammern (3) zur Verbrennung von Brennstoff sowie einem sich jeweils daran anschließendem Mischgehäuse (8a), (8b) und sich daran anschließend einem Innengehäuse (9) sowie einer um eine Welle (12) angeordneten Innengehäusenabe (170), d a d u r c h g e k e n n z e i c h n e t, d a s s die Innengehäusenabe (170) mindestens zwei sich gegenüberliegende Buckel (23a) (23b) aufweist. Combustion chambers (3) for combustion of fuel and a respectively subsequent mixing housing (8a), (8b) and then an inner housing (9) and about a shaft (12) arranged inside housing hub (170), characterized in that the inner housing hub (170) has at least two opposing projections (23a) (23b).
11. Verfahren zur Turbinenanströmung, umfassend zumindest einem Brenner (13) und einer Brennkammer (3), in welcher Brennstoff zu Verbrennungsabgasen (22a, 22b) verbrannt wird, und einem Mischgehäuse (8a, b) sowie ein sich daran anschließendes Innengehäuse (9) zum Führen der11. A method for turbine flow, comprising at least one burner (13) and a combustion chamber (3), in which fuel is burned to combustion exhaust gases (22a, 22b), and a mixing housing (8a, b) and an adjoining inner housing (9) to guide the
Verbrennungsabgase (22a, 22b) zu einer Turbine (5), die im wesentlichen senkrecht zur Strömungsrichtung der Verbrennungsabgase in der Brennkammer (3) angeordnet, wobei im Innengehäuse (9) mittels einer Innengehäusenabe (170) die Verbrennungsabgase (22a, 22b) in Richtung Turbine (5) abgelenkt werden, d a d u r c h g e k e n n z e i c h n e t, d a s s mittels des Aufbringens mindestens eines Buckels (23a, 23b) an der Innengehäusenabe (170) die Strömungsumleitung des Verbrennungsabgasstroms (22a, 22b) im Innengehäuse (9) verbessert wird, so dass eine bessere Turbinenanströmung erzielt wird.Combustion exhaust gases (22a, 22b) to a turbine (5) arranged substantially perpendicular to the flow direction of the combustion exhaust gases in the combustion chamber (3), wherein in the inner housing (9) by means of an inner housing hub (170), the combustion exhaust gases (22a, 22b) in the direction Turbine (5) are deflected, characterized in that by means of applying at least one projection (23a, 23b) on the inner housing hub (170), the flow diversion of the combustion exhaust gas stream (22a, 22b) in the inner housing (9) is improved, so that a better Turbinenanströmung achieved becomes.
12. Verfahren zur Turbinenanströmung nach Anspruch 11, d a d u r c h g e k e n n z e i c h n e t, d a s s die einzelnen12. A method of turbine flow according to claim 11, wherein: a) the individual
Turbinenschaufeln (10,11) gemäß ihrer Auslegung angeströmt werden . Turbine blades (10,11) are flowed according to their interpretation.
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 true EP2318664A1 (en) 2011-05-11
EP2318664B1 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010020487A1 *

Also Published As

Publication number Publication date
EP2318664B1 (en) 2016-05-04
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
EP2179143B1 (en) Gap cooling between combustion chamber wall and turbine wall of a gas turbine installation
EP2582956B1 (en) Gas turbine combustion chamber arrangement of axial type of construction
EP1706597A1 (en) Gas turbine with axially displaceable rotor
WO2006048401A1 (en) Optimised turbine stage for a turbine engine and layout method
DE2454054A1 (en) INTERNAL POWER PLANT AND GAS GENERATOR FOR GAS TURBINE ENGINES
DE102007029004A1 (en) Exhaust gas turbocharger for an internal combustion engine
EP3064706A1 (en) Guide blade assembly for a flow engine with axial flow
DE4446611A1 (en) Combustion chamber
EP2211023A1 (en) Guide vane system for a turbomachine with segmented guide vane carrier
DE102007028742A1 (en) Air supplier, in particular for an air supply system of fuel cells
WO2005019621A1 (en) Diffuser arranged between the compressor and the combustion chamber of a gas turbine
WO1998013584A1 (en) Method of compensating pressure loss in a cooling air guide system in a gas turbine plant
EP0532907B1 (en) Axial turbine
DE102019125654A1 (en) TURBINE SHOVEL
EP2318664B1 (en) Gas turbine assembly with a non-cylindrical transition duct
DE102010027808A1 (en) Swirl generator for a burner
EP1632650B1 (en) Steam turbine
DE1526813A1 (en) Gas mixing plant for turbo engines
WO2003021149A1 (en) Combustion chamber arrangement
EP2157285A1 (en) Gas turbine assembly and method for guiding the flow onto the turbine
EP3029268A1 (en) Turbine rotor blade
EP2157286A1 (en) Gas turbine comprising angled duct and method for guiding the flow onto the turbine
EP2987967B1 (en) Compressor housing for a gas turbine
EP2808612A1 (en) Gas turbine combustion chamber with tangential late lean injection

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