EP2791478A1 - Gas turbine having an exhaust gas diffuser and supporting fins - Google Patents

Gas turbine having an exhaust gas diffuser and supporting fins

Info

Publication number
EP2791478A1
EP2791478A1 EP13700689.6A EP13700689A EP2791478A1 EP 2791478 A1 EP2791478 A1 EP 2791478A1 EP 13700689 A EP13700689 A EP 13700689A EP 2791478 A1 EP2791478 A1 EP 2791478A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
gas turbine
blow
turbine
support ribs
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13700689.6A
Other languages
German (de)
French (fr)
Inventor
Marc Bröker
Tobias Buchal
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 EP13700689.6A priority Critical patent/EP2791478A1/en
Publication of EP2791478A1 publication Critical patent/EP2791478A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like

Definitions

  • the invention relates to a gas turbine with an adjoining a turbine unit exhaust diffuser, whose diffuser channel is bounded by a wall outside and on which a number of inwardly extending hollow support ribs for mounting a radial bearing of the gas turbine are provided, wherein the exhaust gas Diffuser at least one pipeline comprehensive Abblasetechnisch for blown air outflow en ⁇ det, whose inflow-side end is connected to a compressor of the gas turbine.
  • Gas turbines and their modes of operation are well known from the widely available state of the art. They always include an exhaust gas diffuser as part of an exhaust gas line, through which the exhaust gas flowing out of the gas turbine can be continued. The exhaust gas is either led to a chimney, if the gas turbine for single operation, called in English Simple Cycle, is provided. In a combined-cycle power plant - called Combined Cycle in English - leads the Abgasasstre ⁇ bridge the exhaust gas to a boiler, with the help of which the thermal energy contained in the exhaust gas is converted into steam for a steam turbine.
  • the operating point of the exhaust diffuser depends primarily on its volume flow. This is known to be mainly influenced by the ambient temperature, the compressor inlet guide vane position and the firing temperature.
  • the exhaust diffuser should meet several requirements: Firstly, a maximum pressure recovery is required for maximum efficiency at the design point. At the same time, the efficiency will drop only slightly when removed from the off ⁇ legungstician if possible. To the Others, he should have no unsteady operating behavior, which otherwise could affect the mechanical integrity of the power plant ⁇ by vibration excitation. In addition, it should have as uniform a velocity distribution as possible at the outlet to achieve a good boiler efficiency. Equally important is the avoidance of flip-flop effects when changing the operating point during deep part-load operation. Finally ⁇ Finally, the exhaust diffuser should also be small-sized and therefore inexpensive.
  • the object of the invention is therefore to provide a gas turbine with a subsequent to a turbine unit exhaust diffuser, which can counteract the problems mentioned in the prior art.
  • the downstream end of the blow-off line is fluidically connected via the hollow space of the support ribs connected to the hub for forwarding Abblaseluft to the hub and the Abblase poverty is blown on the hub side to the reverse flow behind the hub re ⁇ appear or as Coanda Beam to reduce the tendency to detach at a possibly tapered hub end.
  • the outflow-side end of the blow-off line is fluidically connected to the cavity of the support ribs, wherein the support ribs have openings for blowing the blow-off air into the diffuser channel.
  • the support ribs which Abblase poverty can be specifically used for reducing the detachments of the then heavily misused flocked support ribs in partial load operation. Furthermore, in this way, the bearing star formed by the support ribs and parts thereof-for example, their sheet metal clothing-can be specifically cooled. This allows an increase in the turbine outlet temperature in the part-load operation, compared to the rated load operation, whereby in part-load operation again the lowering of the flame temperature and the associated increase in the CO values of the exhaust gas can be counteracted. It should be noted that the blowing out of the blow-off air through the openings arranged in the support ribs can also be provided independently of the blowing through the hub.
  • the invention will be explained in more detail with reference to a single FIGURE.
  • the single embodiment shows a gas turbine in a longitudinal section.
  • FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
  • the gas turbine 10 has inside a rotatably mounted about a rotation axis 12 rotor 14, which is also referred to as a turbine runner.
  • a rotation axis 12 rotor 14 Along the rotor 14 follow one another an intake housing 16, a Axialturbover Noticer 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetric symmetrically arranged to each other burners 22, a turbine unit 24 and a turbine outlet housing 26 to the turbine outlet housing 26 of the gas turbine 10 is followed by a not shown turbines -Abgas distributor on. Both components are part of the gas turbine exhaust diffuser 21.
  • the gas turbine can also be equipped with multiple tube combustion chambers.
  • the Axialturbover Noticer 18 comprises a ring-shaped channel compressor in successive cascade constricting compressor stages from Laufschaufei- and vane ⁇ wreaths.
  • the rotor blades 14 arranged on the blades 27 are located with their free-ending blade tips of an outer channel wall of the compressor passage opposite.
  • the compressor channel opens via a compressor outlet diffuser 36 in a ple number 38.
  • the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas channel 30 of the turbine unit 24.
  • Turbi ⁇ nenech 24 are four successive turbine arranged steps 32.
  • a generator or a working machine (each not shown) is coupled.
  • the turbine output housing 26 of the gas turbine 10 is followed by a turbine exhaust manifold. Both components are part of the gas turbine exhaust diffuser 21. Downstream of the Turbi ⁇ nen exhaust manifold, an equally not dargestell ⁇ tes exhaust gas system is provided. This and the gas turbine exhaust diffuser 21 form the exhaust gas diffuser system.
  • an inflow-side annular diffuser channel 33 is provided, which is bounded radially on the outside by a conical channel wall 40.
  • a conical channel wall 40 On the channel wall 40 along the periphery of the diffuser channel 33 six
  • Support ribs 35 distributed, of which only one is shown in longitudinal section. There may also be a different number of support ribs.
  • Each support rib 35 has in its interior a support 37, which is protected by a Blechumposed 39 from direct contact with exhaust gas.
  • the Blechumposed 39 has a leading edge 41 and a Ab ⁇ strömkante 43, which is profiled aero ⁇ dynamically in cross section analogous to the profile contour of a blade of a compressor blade.
  • a hub 48 is arranged, which forms a housing for an internally disposed turbine-side radial bearing 51.
  • blow-off 47 a part of the compressor mass flow feed ⁇ bar.
  • the blow-off line 47 comprises three pipes, of which only one pipe is shown. It can also be provided more than three or fewer pipes.
  • the pipes, not shown, are distributed along the circumference of the gas turbine 10.
  • a valve is also provided as an actuator 46 for closing and partially or completely opening the pipelines. All pipes connect the compressor 18 or the plenum 38 with the cavities 45 to supply this blow-off air.
  • a plurality of openings 49 are provided, through which the supporting rib, a ⁇ can be brought 35 supplied Abblase Kunststoff in the diffuser channel 33rd
  • openings 49 may be provided for blowing blown air in the hub. In particular, the latter embodiment is suitable for avoiding return flow zones downstream of the hub 48.
  • the operation of the gas turbine 10 is designed so that in nominal load operation only such an amount of blow-off air flows out of the openings 49 as is necessary to prevent penetration of the exhaust gas into the openings 49. If the power output of the gas turbine is lowered below a predetermined value, which is arranged in the Abblaselei ⁇ tung actuators 47 are further opened 46 so that the Abblasemassenstrom significantly increases.
  • the predetermined value may, for example, 80%, 70%, 50% or even a ande ⁇ ren percentage of gas turbine rated power amount.
  • detachment at the support ribs 35 can be avoided by this measure. ner Benedictanströmung can occur because of a reduced exhaust gas mass flow.
  • the percentage of combustion air in the fuel-air mixture is reduced, which leads to a higher combustion temperature and can keep CO emissions to a lower level.
  • blowing out the blow-off air through the hub 48 can also remindströmzonen downstream of the hub 48 can be avoided.
  • the invention proposes a gas turbine 10 with an exhaust gas diffuser 21 adjoining a turbine unit 24, whose diffuser channel 33 is bounded on the outside by a channel wall 40 and on which a number of inwardly extending hollow support ribs 35 for fastening a radial bearing 51 the gas turbine 10 are provided, wherein at the exhaust gas diffuser 21 at least one pipes comprehensive Abblasetechnisch 47 for blown air ends outflow, the ⁇ sen inflow end is connected to a compressor 18 of the gas turbine 10.
  • the support ribs 35 have a hub 48 at their inner end, at the axial end thereof further openings 49 for blowing out the blow-off air into the diffuser duct are pre ⁇ seen.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

The invention relates to a gas turbine (10) having an exhaust gas diffuser (21) connected to a turbine unit (24), wherein the gas diffuser channel (33) of the gas diffuser is delimited on the outside by a channel wall (40) and is provided with a plurality of hollow supporting fins (35) extending inward for fastening a radial bearing (51) of the gas turbine (10), wherein at least one blow-off line (47) for blow-off air comprising at least one pipeline ends at the outlet side on the exhaust gas diffuser (21) and the end of the exhaust gas diffuser on the inlet side is connected to a compressor (18) of the gas turbine (10). In order to at least partially compensate for the incorrect incident flow of the supporting fins (35), more particularly in partial load operation, it is proposed that the supporting fins (35) have a hub (48) on the inner end thereof, the axial end of said hub being provided with additional openings (49) for blowing out the blow-off air in the diffuser channel.

Description

Beschreibung description
Gasturbine mit einem Abgas-Diffusor und Stützrippen Gas turbine with an exhaust diffuser and support ribs
Die Erfindung betrifft eine Gasturbine mit einem sich an eine Turbineneinheit anschließenden Abgas-Diffusor, dessen Diffu- sorkanal von einer Wand außen begrenzt ist und an der eine Anzahl von sich nach Innen erstreckenden hohlen Stützrippen zur Befestigung eines Radiallagers der Gasturbine vorgesehen sind, wobei am Abgas-Diffusor zumindest eine Rohrleitungen umfassende Abblaseleitung für Abblaseluft ausströmseitig en¬ det, dessen einströmseitiges Ende mit einem Verdichter der Gasturbine verbunden ist. The invention relates to a gas turbine with an adjoining a turbine unit exhaust diffuser, whose diffuser channel is bounded by a wall outside and on which a number of inwardly extending hollow support ribs for mounting a radial bearing of the gas turbine are provided, wherein the exhaust gas Diffuser at least one pipeline comprehensive Abblaseleitung for blown air outflow en ¬ det, whose inflow-side end is connected to a compressor of the gas turbine.
Gasturbinen und deren Betriebsweisen sind aus dem umfangreich verfügbaren Stand der Technik bestens bekannt. Sie umfassen stets einen Abgas-Diffusor als Teil einer Abgasstrecke, durch den das aus der Gasturbine abströmende Abgas weitergeführt werden kann. Das Abgas wird entweder zu einem Schornstein geführt, sofern die Gasturbine zum Alleinbetrieb, im Englischen Simple Cycle genannt, vorgesehen ist. Bei einem GuD-Kraftwerk - im Englischen Combined Cycle genannt - führt die Abgasstre¬ cke das Abgas zu einem Kessel, mit dessen Hilfe die im Abgas enthaltene thermische Energie in Dampf für eine Dampfturbine umgewandelt wird. Gas turbines and their modes of operation are well known from the widely available state of the art. They always include an exhaust gas diffuser as part of an exhaust gas line, through which the exhaust gas flowing out of the gas turbine can be continued. The exhaust gas is either led to a chimney, if the gas turbine for single operation, called in English Simple Cycle, is provided. In a combined-cycle power plant - called Combined Cycle in English - leads the Abgasasstre ¬ bridge the exhaust gas to a boiler, with the help of which the thermal energy contained in the exhaust gas is converted into steam for a steam turbine.
Der Betriebspunkt des Abgas-Diffusors hängt in erster Linie von seinem Volumenstrom ab. Dieser wird bekanntermaßen haupt- sächlich von der Umgebungstemperatur, der Verdichter-Einlass- leitschaufelstellung sowie der Befeuerungstemperatur beein- flusst . The operating point of the exhaust diffuser depends primarily on its volume flow. This is known to be mainly influenced by the ambient temperature, the compressor inlet guide vane position and the firing temperature.
Der Abgas-Diffusor sollte mehrere Anforderungen erfüllen: Zum Einen ist ein maximaler Druckrückgewinn zur Erzielung eines maximalen Wirkungsgrades im Auslegungspunkt erforderlich. Gleichzeitig soll der Wirkungsgrad bei Entfernung vom Aus¬ legungspunkt nach Möglichkeit nur geringfügig abfallen. Zum Anderen sollte er kein instationäres Betriebsverhalten aufweisen, was ansonsten die mechanische Integrität der Kraft¬ werksanlage durch Schwingungsanregung beeinträchtigen könnte. Darüber hinaus sollte er eine möglichst gleichmäßige Ge- schwindigkeitsverteilung am Austritt zur Erreichung eines guten Kesselwirkungsgrades aufweisen. Ebenso bedeutsam ist die Vermeidung von Flip-Flop-Effekten bei Änderung des Betriebspunktes während des tiefen Teillastbetriebs. Schluss¬ endlich sollte der Abgas-Diffusor zudem auch kleinbauend und somit kostengünstig sein. The exhaust diffuser should meet several requirements: Firstly, a maximum pressure recovery is required for maximum efficiency at the design point. At the same time, the efficiency will drop only slightly when removed from the off ¬ legungspunkt if possible. To the Others, he should have no unsteady operating behavior, which otherwise could affect the mechanical integrity of the power plant ¬ by vibration excitation. In addition, it should have as uniform a velocity distribution as possible at the outlet to achieve a good boiler efficiency. Equally important is the avoidance of flip-flop effects when changing the operating point during deep part-load operation. Finally ¬ Finally, the exhaust diffuser should also be small-sized and therefore inexpensive.
Von besonderer Bedeutung für eine optimale Diffusorströmung ist das Vermeiden von Ablöse- und Rückströmzonen, sowohl an der Außenwand als auch am Übergang vom Abgas-Diffusor zum Kesseleinlauf. Sofern diese dennoch auftreten, sollte ihre Größe vergleichsweise klein sein. Die Ablösungen an der Innenfläche der glatten Diffusor-Außenwand sind zumeist ver¬ ursacht durch eine zu geringe lokale Strömungsenergie, die dem stromab ansteigenden Druck nicht entgegenwirken kann. Ursächlich hierfür ist neben dem Öffnungswinkel des Diffusors die Abströmung an der letzten Turbinenlaufschaufelreihe und insbesondere die Überströmung an deren Schaufelspitzen. Rückstromzonen können sich ggf. im Teillastbetrieb ausbilden, insbesondere hinter der Nabe und an der Außenwand. Dabei kön¬ nen Sie so weit stromab reichen, dass es selbst im Bereich des Kesseleintritts zu Zonen stromauf gerichteter Strömung kommt. Bei der Verwendung von Nachbrennern kann durch Rück- strömungen ein Flammenrückschlag erzeugt werden, was die kom¬ binierte Betriebsweise von Gasturbinen und Nachbrennern einschränken könnte. Of particular importance for optimum diffuser flow is the avoidance of separation and backflow zones, both at the outer wall and at the transition from the exhaust gas diffuser to the boiler inlet. If these occur nevertheless, their size should be comparatively small. The separations on the inner surface of the smooth diffuser outer wall are mostly ver ¬ ursacht by insufficient local flow of energy which can not counteract the increasing pressure downstream. The reason for this, in addition to the opening angle of the diffuser, is the outflow at the last turbine blade row and in particular the overflow at the blade tips. If necessary, backflow zones can be formed in partial load operation, in particular behind the hub and on the outer wall. Here, Kings ¬ nen They range as far downstream that it is even in the boiler inlet upstream to areas directed flow. When using afterburners, a flashback can be produced by return currents, which could limit the com bined ¬ operation of gas turbines and afterburners.
Um diesen aerodynamischen Phänomenen entgegenzuwirken ist es bekannt, im Teillastbetrieb der Gasturbine der Diffusorströ¬ mung Teile des Verdichtermassenstroms über Verdichterentnah- men und mehrere Abblaseleitungen direkt zuzuführen. Dabei sind die Mündungen der Abblaseleitungen in den Diffusor meist kostenmäßig optimiert, so dass diese eher diagonal auf der Mantelfläche des Diffusors angeordnet sind. Durch die Ausbla- sung an wenigen Umfangsstellen kommt es innerhalb der Diffu- sorströmung zudem zu kalten Strähnen. Im Zusammenhang mit einer instationären Strömung im Diffusor führt dies zu einer instationären thermischen Beanspruchung der Diffusorwände und begünstigt so die Rissbildung dort. To counteract these aerodynamic phenomena it is known, men parts of the compressor mass flow at part load operation of the gas turbine of Diffusorströ ¬ tion about Verdichterentnah- and feed multiple discharge pipes directly. The mouths of the blow-off lines in the diffuser are usually optimized in terms of cost, so that they are arranged rather diagonally on the lateral surface of the diffuser. Due to the blown At a few peripheral points, cold streaks also occur within the diffuser flow. In connection with a transient flow in the diffuser, this leads to a transient thermal stress on the diffuser walls and thus favors the formation of cracks there.
Aufgabe der Erfindung ist daher die Bereitstellung einer Gasturbine mit einem sich an eine Turbineneinheit anschließenden Abgas-Diffusor, welcher den im Stand der Technik genannten Problemen entgegenwirken kann. The object of the invention is therefore to provide a gas turbine with a subsequent to a turbine unit exhaust diffuser, which can counteract the problems mentioned in the prior art.
Die auf die Gasturbine gerichtete Aufgabe wird mit einer sol¬ chen gemäß den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben und können in beliebiger Weise miteinander kombiniert werden. The object directed to the gas turbine is achieved with a sol ¬ chen according to the features of claim 1. Advantageous embodiments are specified in the subclaims and can be combined with one another in any desired manner.
Erfindungsgemäß ist vorgesehen, dass das ausströmseitige Ende der Abblaseleitung über den Hohlraum der Stützrippen mit der Nabe strömungstechnisch verbunden ist zur Weiterleitung von Abblaseluft bis in die Nabe und die Abblaseluft nabenseitig ausgeblasen wird, um die Rückströmzone hinter der Nabe zu re¬ duzieren oder um als Coanda-Strahl die Ablöseneigung an einem ggf. konisch zulaufenden Nabenende zu reduzieren. Gemäß einer vorteilhaften Weiterbildung ist das ausströmseitige Ende der Abblaseleitung mit dem Hohlraum der Stützrippen strömungstechnisch verbunden, wobei die Stützrippen Öffnungen zum Ausblasen der Abblaseluft in den Diffusorkanal aufweisen. Durch die Führung der Abblaseluft in die Stützrippen des hin- teren Lagersterns und die vorzugsweise Ausblasung an der Ab¬ strömkante der Stützrippen kann die Abblaseluft gezielt dafür genutzt werden, im Teillastbetrieb die Ablösungen an den dann stark fehlangeströmten Stützrippen zu reduzieren. Ferner lässt sich auf diese Weise der von den Stützrippen gebildete Lagerstern und Teile davon - beispielsweise deren Blechum- kleidung - gezielt kühlen. Dies ermöglicht eine Anhebung der Turbinenaustrittstemperatur im Teillastbetrieb, verglichen mit dem Nennlastbetrieb, wodurch im Teillastbetrieb wiederum dem Absinken der Flammentemperatur und dem damit verbundenen Ansteigen der CO-Werte des Abgases entgegengewirkt werden kann . Es sei bemerkt, dass die Ausblasung der Abblaseluft durch die in den Stützrippen angeordneten Öffnungen auch unabhängig von der Ausblasung durch die Nabe vorgesehen sein kann. According to the invention it is provided that the downstream end of the blow-off line is fluidically connected via the hollow space of the support ribs connected to the hub for forwarding Abblaseluft to the hub and the Abblaseluft is blown on the hub side to the reverse flow behind the hub re ¬ duce or as Coanda Beam to reduce the tendency to detach at a possibly tapered hub end. According to an advantageous development, the outflow-side end of the blow-off line is fluidically connected to the cavity of the support ribs, wherein the support ribs have openings for blowing the blow-off air into the diffuser channel. By guiding the Abblaseluft in the support ribs of the back direct bearing star and preferably blow-out at the From ¬ strömkante the support ribs which Abblaseluft can be specifically used for reducing the detachments of the then heavily misused flocked support ribs in partial load operation. Furthermore, in this way, the bearing star formed by the support ribs and parts thereof-for example, their sheet metal clothing-can be specifically cooled. This allows an increase in the turbine outlet temperature in the part-load operation, compared to the rated load operation, whereby in part-load operation again the lowering of the flame temperature and the associated increase in the CO values of the exhaust gas can be counteracted. It should be noted that the blowing out of the blow-off air through the openings arranged in the support ribs can also be provided independently of the blowing through the hub.
Die Erfindung wird anhand einer einzigen Figur näher erläu- tert. Das einzige Ausführungsbeispiel zeigt eine Gasturbine in einem Längsteilschnitt. The invention will be explained in more detail with reference to a single FIGURE. The single embodiment shows a gas turbine in a longitudinal section.
Figur 1 zeigt eine stationäre Gasturbine 10 in einem Längs- teilschnitt. Die Gasturbine 10 weist im Innern einen um eine Rotationsachse 12 drehgelagerten Rotor 14 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 14 folgen aufeinander ein Ansauggehäuse 16, ein Axialturboverdichter 18, eine torusartige Ringbrennkammer 20 mit mehreren rotati- onssymmetrisch zueinander angeordneten Brennern 22, eine Turbineneinheit 24 und ein Turbinenausgangsgehäuse 26. An das Turbinenausgangsgehäuse 26 der Gasturbine 10 schließt sich ein nicht weiter dargestellter Turbinen-Abgas-Verteiler an. Beide Komponenten sind Teil des Gasturbinen-Abgas-Diffusors 21. Anstelle der Ringbrennkammer kann die Gasturbine auch mit mehreren Rohrbrennkammern ausgestattet sein. FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section. The gas turbine 10 has inside a rotatably mounted about a rotation axis 12 rotor 14, which is also referred to as a turbine runner. Along the rotor 14 follow one another an intake housing 16, a Axialturboverdichter 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetric symmetrically arranged to each other burners 22, a turbine unit 24 and a turbine outlet housing 26 to the turbine outlet housing 26 of the gas turbine 10 is followed by a not shown turbines -Abgas distributor on. Both components are part of the gas turbine exhaust diffuser 21. Instead of the annular combustion chamber, the gas turbine can also be equipped with multiple tube combustion chambers.
Der Axialturboverdichter 18 umfasst einen ringförmig ausgebildeten Verdichterkanal mit darin kaskadisch aufeinanderfol- genden Verdichterstufen aus Laufschaufei- und Leitschaufel¬ kränzen. Die am Rotor 14 angeordneten Laufschaufeln 27 liegen mit ihren frei endenden Schaufelblattspitzen einer äußeren Kanalwand des Verdichterkanals gegenüber. Der Verdichterkanal mündet über einen Verdichterausgangsdiffusor 36 in einem Ple- num 38. Darin ist die Ringbrennkammer 20 mit ihrem Verbrennungsraum 28 vorgesehen, der mit einem ringförmigen Heißgaskanal 30 der Turbineneinheit 24 kommuniziert. In der Turbi¬ neneinheit 24 sind vier hintereinandergeschaltete Turbinen- stufen 32 angeordnet. Am Rotor 14 ist ein Generator oder eine Arbeitsmaschine (jeweils nicht dargestellt) angekoppelt. The Axialturboverdichter 18 comprises a ring-shaped channel compressor in successive cascade constricting compressor stages from Laufschaufei- and vane ¬ wreaths. The rotor blades 14 arranged on the blades 27 are located with their free-ending blade tips of an outer channel wall of the compressor passage opposite. The compressor channel opens via a compressor outlet diffuser 36 in a ple number 38. Therein, the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas channel 30 of the turbine unit 24. In the Turbi ¬ neneinheit 24 are four successive turbine arranged steps 32. On the rotor 14, a generator or a working machine (each not shown) is coupled.
An das Turbinenausgangsgehäuse 26 der Gasturbine 10 schließt sich ein Turbinen-Abgas-Verteiler an. Beide Komponenten sind Teil des Gasturbinen-Abgas-Diffusors 21. Stromab des Turbi¬ nen-Abgas-Verteilers ist ein ebenso nicht weiter dargestell¬ tes Abgas-Gas-System vorgesehen. Dieses und der Gasturbinen- Abgas-Diffusor 21 bilden das Abgas-Diffusor-System. The turbine output housing 26 of the gas turbine 10 is followed by a turbine exhaust manifold. Both components are part of the gas turbine exhaust diffuser 21. Downstream of the Turbi ¬ nen exhaust manifold, an equally not dargestell ¬ tes exhaust gas system is provided. This and the gas turbine exhaust diffuser 21 form the exhaust gas diffuser system.
Im Gasturbinen-Abgas-Diffusor 21 ist ein einströmseitig ringförmiger Diffusorkanal 33 vorgesehen, der radial außen von einer konischen Kanalwand 40 begrenzt ist. An der Kanalwand 40 sind entlang des Umfangs des Diffusorkanais 33 sechs In the gas turbine exhaust gas diffuser 21, an inflow-side annular diffuser channel 33 is provided, which is bounded radially on the outside by a conical channel wall 40. On the channel wall 40 along the periphery of the diffuser channel 33 six
Stützrippen 35 verteilt, von denen lediglich eine im Längsschnitt dargestellt ist. Es kann auch eine andere Anzahl an Stützrippen vorhanden sein. Jede Stützrippe 35 weist in ihrem Inneren eine Stütze 37 auf, welche durch eine Blechumkleidung 39 vor dem direkten Kontakt mit Abgas geschützt ist. Die Blechumkleidung 39 weist eine Anströmkante 41 und eine Ab¬ strömkante 43 auf, wobei diese analog der Profilkontur eines Schaufelblatts einer Verdichterschaufel im Querschnitt aero¬ dynamisch profiliert ist. An den inneren Enden der Stützrippen 35 ist eine Nabe 48 angeordnet, welche ein Gehäuse für ein im Inneren angeordnetes turbinenseitiges Radiallager 51 bildet. Trotz der Stütze 37 ist im Inneren der Blechumklei¬ dung 39 noch ein Hohlraum 45 vorhanden. Diesem ist über eine Abblaseleitung 47 ein Teil des Verdichtermassenstroms zuführ¬ bar. Die Abblaseleitung 47 umfasst drei Rohrleitungen, von denen lediglich eine Rohrleitung dargestellt ist. Es können auch mehr als drei oder weniger Rohrleitungen vorgesehen sein. Die nicht dargestellten Rohrleitungen sind entlang des Umfangs der Gasturbine 10 verteilt. In jeder Rohrleitung ist zudem ein Ventil als Stellorgan 46 zum Schließen und teilwei- sem oder vollständigem Öffnen der Rohrleitungen vorgesehen. Alle Rohrleitungen verbinden den Verdichter 18 oder das Plenum 38 mit den Hohlräumen 45, um diesen Abblaseluft zuzuführen . In der Abströmkante 43 der Stützrippe 35 und/oder im stromab- wärtigen Bereich der konvexen Saugseite der Stützrippen (35) sind mehrere Öffnungen 49 vorgesehen, über die die der Stütz- rippe 35 zugeführte Abblaseluft in den Diffusorkanal 33 ein¬ gebracht werden kann. Auch unabhängig von dem Vorhandensein der Öffnungen 49 in den Stützrippen 35 können in der Nabe 48 Öffnungen 49 zum Ausblasen von Abblaseluft vorgesehen sein. Insbesondere letztere Ausgestaltung eignet sich dazu, Rück- strömzonen stromab der Nabe 48 zu vermeiden. Support ribs 35 distributed, of which only one is shown in longitudinal section. There may also be a different number of support ribs. Each support rib 35 has in its interior a support 37, which is protected by a Blechumkleidung 39 from direct contact with exhaust gas. The Blechumkleidung 39 has a leading edge 41 and a Ab ¬ strömkante 43, which is profiled aero ¬ dynamically in cross section analogous to the profile contour of a blade of a compressor blade. At the inner ends of the support ribs 35, a hub 48 is arranged, which forms a housing for an internally disposed turbine-side radial bearing 51. Despite the support 37 inside the Blechumklei ¬ extension 39 nor a cavity 45 is present. This is via a blow-off 47 a part of the compressor mass flow feed ¬ bar. The blow-off line 47 comprises three pipes, of which only one pipe is shown. It can also be provided more than three or fewer pipes. The pipes, not shown, are distributed along the circumference of the gas turbine 10. In each pipeline, a valve is also provided as an actuator 46 for closing and partially or completely opening the pipelines. All pipes connect the compressor 18 or the plenum 38 with the cavities 45 to supply this blow-off air. In the trailing edge 43 of the support rib 35 and / or in the downstream passageway wärtigen region of the convex suction side of the support ribs (35) a plurality of openings 49 are provided, through which the supporting rib, a ¬ can be brought 35 supplied Abblaseluft in the diffuser channel 33rd Also, regardless of the presence of the openings 49 in the support ribs 35 48 openings 49 may be provided for blowing blown air in the hub. In particular, the latter embodiment is suitable for avoiding return flow zones downstream of the hub 48.
Im Betrieb der Gasturbine 10 saugt der Axialturboverdichter 18 durch das Ansauggehäuse 16 als zu verdichtendes Medium Um¬ gebungsluft 34 an und verdichtet diese. Die verdichtete Luft wird durch den Verdichterausgangsdiffusor 36 in das Plenum 38 geführt, von wo aus es in die Brenner 22 einströmt. Über die Brenner 22 gelangt auch Brennstoff in den Verbrennungsraum 28. Dort wird der Brennstoff unter Zugabe der verdichteten Luft zu einem Heißgas M verbrannt. Das Heißgas M strömt an- schließend in den Heißgaskanal 30, wo es sich arbeitsleistend an den Turbinenschaufeln der Turbineneinheit 24 entspannt. Die währenddessen freigesetzte Energie wird vom Rotor 14 auf¬ genommen und einerseits zum Antrieb des Axialturboverdichters 18 und andererseits zum Antrieb einer Arbeitsmaschine oder elektrischen Generators genutzt. In operation of the gas turbine 10 of the Axialturboverdichter 18 sucked through the intake 16 as the medium to be compressed in order ¬ bient 34 and compresses it. The compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22. Fuel also passes into the combustion space 28 via the burners 22. There, the fuel is burned to a hot gas M with the addition of the compressed air. The hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24. During which the energy released is removed from the rotor 14 on the one hand, and ¬ for driving the Axialturboverdichters 18 and on the other hand for driving a working machine or the electric generator used.
Der Betrieb der Gasturbine 10 ist so ausgestaltet, dass im Nennlastbetrieb lediglich eine derartige Menge an Abblaseluft aus den Öffnungen 49 ausströmt wie es zur Vermeidung von ei- nem Eindringen des Abgases in die Öffnungen 49 erforderlich ist. Wird die abgegebene Leistung der Gasturbine unter einen vorbestimmten Wert abgesenkt, werden die in der Abblaselei¬ tung 47 angeordneten Stellorgane 46 weiter geöffnet, so dass der Abblasemassenstrom signifikant zunimmt. Der vorbestimmte Wert kann beispielsweise 80%, 70%, 50% oder auch einen ande¬ ren Prozentsatz der Gasturbinen-Nennleistung betragen. Durch diese Maßnahme können einerseits Ablösungen an den Stützrippen 35 vermieden werden, welche im Teillastbetrieb wegen ei- ner Fehlanströmung wegen eines verringerten Abgas-Massenstroms auftreten können. Zudem wird der prozentuale Anteil an Verbrennungsluft im Brennstoff-Luft-Gemisch reduziert, was zu einer höheren Verbrennungstemperatur führt und CO-Emissionen auf einen geringeren Wert halten kann. Durch das Ausblasen der Abblaseluft durch die Nabe 48 können zudem Rückströmzonen stromab der Nabe 48 vermieden werden. The operation of the gas turbine 10 is designed so that in nominal load operation only such an amount of blow-off air flows out of the openings 49 as is necessary to prevent penetration of the exhaust gas into the openings 49. If the power output of the gas turbine is lowered below a predetermined value, which is arranged in the Abblaselei ¬ tung actuators 47 are further opened 46 so that the Abblasemassenstrom significantly increases. The predetermined value may, for example, 80%, 70%, 50% or even a ande ¬ ren percentage of gas turbine rated power amount. On the one hand, detachment at the support ribs 35 can be avoided by this measure. ner Fehlanströmung can occur because of a reduced exhaust gas mass flow. In addition, the percentage of combustion air in the fuel-air mixture is reduced, which leads to a higher combustion temperature and can keep CO emissions to a lower level. By blowing out the blow-off air through the hub 48 can also Rückströmzonen downstream of the hub 48 can be avoided.
Insgesamt wird mit der Erfindung eine Gasturbine 10 mit einem sich an eine Turbineneinheit 24 anschließenden Abgas-Diffusor 21 vorgeschlagen, dessen Diffusorkanal 33 von einer Kanalwand 40 außen begrenzt ist und an der eine Anzahl von sich nach innen erstreckenden hohlen Stützrippen 35 zur Befestigung eines Radiallagers 51 der Gasturbine 10 vorgesehen sind, wobei am Abgas-Diffusor 21 zumindest eine Rohrleitungen umfassende Abblaseleitung 47 für Abblaseluft ausströmseitig endet, des¬ sen einströmseitiges Ende mit einem Verdichter 18 der Gasturbine 10 verbunden ist. Um insbesondere im Teillastbetrieb den durch die Fehlanströmung der Stützrippen 35 ausgelösten Wir- kungsgradverlust zumindest teilweise zu kompensieren, ist vorgesehen, dass die Stützrippen 35 an ihrem inneren Ende eine Nabe 48 aufweisen, an deren axialen Ende weitere Öffnungen 49 zum Ausblasen der Abblaseluft in den Diffusorkanal vorge¬ sehen sind. Overall, the invention proposes a gas turbine 10 with an exhaust gas diffuser 21 adjoining a turbine unit 24, whose diffuser channel 33 is bounded on the outside by a channel wall 40 and on which a number of inwardly extending hollow support ribs 35 for fastening a radial bearing 51 the gas turbine 10 are provided, wherein at the exhaust gas diffuser 21 at least one pipes comprehensive Abblaseleitung 47 for blown air ends outflow, the ¬ sen inflow end is connected to a compressor 18 of the gas turbine 10. In order to at least partially compensate for the loss of efficiency caused by the false flow of the support ribs 35, in particular during partial load operation, it is provided that the support ribs 35 have a hub 48 at their inner end, at the axial end thereof further openings 49 for blowing out the blow-off air into the diffuser duct are pre ¬ seen.

Claims

Patentansprüche claims
1. Gasturbine (10) mit einem sich an eine Turbineneinheit (24) anschließenden Abgas-Diffusor (21), dessen Diffusor- kanal (33) von einer Kanalwand (40) außen begrenzt ist und an der eine Anzahl von sich nach innen erstreckenden hohlen Stützrippen (35) zur Befestigung eines Radiallagers (51) der Gasturbine (10) vorgesehen sind, A gas turbine (10) having an exhaust gas diffuser (21) adjoining a turbine unit (24), the diffuser channel (33) of which is externally delimited by a duct wall (40) and having a number of inwardly extending cavities Supporting ribs (35) are provided for fastening a radial bearing (51) of the gas turbine (10),
wobei am Abgas-Diffusor (21) zumindest eine Rohrleitungen umfassende Abblaseleitung (47) für Abblaseluft ausströmsei- tig endet, dessen einströmseitiges Ende mit einem Verdich¬ ter der Gasturbine (10) verbunden ist, wherein at least one piping comprising the gas diffuser (21) blow-off line (47) for Abblaseluft ausströmsei- tig ends whose einströmseitiges end is connected to a compaction ¬ ter of the gas turbine (10),
wobei die Stützrippen (35) an ihrem inneren Ende eine Nabe (48) aufweisen, die über den Hohlraum der jeweiligen Stützrippe (35) mit dem ausströmseitigen Ende der Abblaseleitung strömungstechnisch verbunden ist,  wherein the support ribs (35) have at their inner end a hub (48) which is fluidly connected via the cavity of the respective support rib (35) with the outflow end of the blow-off line,
dadurch gekennzeichnet, dass  characterized in that
am axialen Ende der Nabe (48) weitere Öffnungen (49) zum Ausblasen der Abblaseluft in den Diffusorkanal (33) vorge¬ sehen sind. at the axial end of the hub (48) further openings (49) for blowing the blow-off air into the diffuser channel (33) are pre ¬ seen.
2. Gasturbine (10) nach Anspruch 1, 2. Gas turbine (10) according to claim 1,
bei der die Öffnungen (49) an den Stützrippen (35) ausschließlich nabenseitig verteilt sind.  in which the openings (49) on the support ribs (35) are distributed exclusively on the hub side.
3. Gasturbine (10) nach Anspruch 1 oder 2, 3. Gas turbine (10) according to claim 1 or 2,
bei der die Öffnungen (49) an einer Abströmkante der Stützrippen (35) und/oder im stromabwärtigen Bereich der konvexen Saugseite der Stützrippen (35) angeordnet sind.  wherein the openings (49) are arranged on a trailing edge of the support ribs (35) and / or in the downstream region of the convex suction side of the support ribs (35).
4. Gasturbine (10) nach Anspruch 1, 2 oder 3, 4. gas turbine (10) according to claim 1, 2 or 3,
bei der die Stützrippen (35) Öffnungen (49) zum Ausblasen der Abblaseluft in den Diffusorkanal (33) aufweisen.  in which the support ribs (35) have openings (49) for blowing the blow-off air into the diffuser channel (33).
EP13700689.6A 2012-02-28 2013-01-15 Gas turbine having an exhaust gas diffuser and supporting fins Withdrawn EP2791478A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13700689.6A EP2791478A1 (en) 2012-02-28 2013-01-15 Gas turbine having an exhaust gas diffuser and supporting fins

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12157273.9A EP2634381A1 (en) 2012-02-28 2012-02-28 Gas turbine with an exhaust gas diffuser and support ribs
PCT/EP2013/050610 WO2013127553A1 (en) 2012-02-28 2013-01-15 Gas turbine having an exhaust gas diffuser and supporting fins
EP13700689.6A EP2791478A1 (en) 2012-02-28 2013-01-15 Gas turbine having an exhaust gas diffuser and supporting fins

Publications (1)

Publication Number Publication Date
EP2791478A1 true EP2791478A1 (en) 2014-10-22

Family

ID=47594704

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12157273.9A Withdrawn EP2634381A1 (en) 2012-02-28 2012-02-28 Gas turbine with an exhaust gas diffuser and support ribs
EP13700689.6A Withdrawn EP2791478A1 (en) 2012-02-28 2013-01-15 Gas turbine having an exhaust gas diffuser and supporting fins

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP12157273.9A Withdrawn EP2634381A1 (en) 2012-02-28 2012-02-28 Gas turbine with an exhaust gas diffuser and support ribs

Country Status (7)

Country Link
US (1) US20140373504A1 (en)
EP (2) EP2634381A1 (en)
JP (1) JP2015508860A (en)
KR (1) KR20140127291A (en)
CN (1) CN104145089B (en)
IN (1) IN2014DN06201A (en)
WO (1) WO2013127553A1 (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9488191B2 (en) 2013-10-30 2016-11-08 Siemens Aktiengesellschaft Gas turbine diffuser strut including coanda flow injection
EP2896793A1 (en) 2014-01-21 2015-07-22 Alstom Technology Ltd Method of operating a gas turbine assembly and the gas turbine assembly
EP3147465A1 (en) * 2015-09-24 2017-03-29 Siemens Aktiengesellschaft Support of a machine, rotating machine engine and a method for assembling of such a rotating machine
JP6563312B2 (en) * 2015-11-05 2019-08-21 川崎重工業株式会社 Extraction structure of gas turbine engine
US9964035B2 (en) * 2015-12-15 2018-05-08 General Electric Company Power plant including exhaust gas coolant injection system and steam generating system via turbine extraction
US10072573B2 (en) * 2015-12-15 2018-09-11 General Electric Company Power plant including an ejector and steam generating system via turbine extraction
US9970354B2 (en) * 2015-12-15 2018-05-15 General Electric Company Power plant including an ejector and steam generating system via turbine extraction and compressor extraction
US9890710B2 (en) * 2015-12-15 2018-02-13 General Electric Company Power plant with steam generation via combustor gas extraction
US9976479B2 (en) * 2015-12-15 2018-05-22 General Electric Company Power plant including a static mixer and steam generating system via turbine extraction and compressor extraction
US10883387B2 (en) * 2016-03-07 2021-01-05 General Electric Company Gas turbine exhaust diffuser with air injection
CN108180045A (en) * 2018-02-07 2018-06-19 上海电气电站设备有限公司 Gas-steam Combined Cycle peak regulation phase modulation shaft system of unit support construction
DE102018217824A1 (en) 2018-10-18 2020-04-23 Siemens Aktiengesellschaft Method for assembling a gas turbine arrangement on a foundation of a power plant and gas turbine arrangement
CN111927581B (en) * 2020-09-08 2022-07-12 杭州汽轮机股份有限公司 Multi-surface supported welding exhaust cylinder of industrial steam turbine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2744722A (en) * 1951-04-06 1956-05-08 Gen Motors Corp Turbine bearing support

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US6266954B1 (en) * 1999-12-15 2001-07-31 General Electric Co. Double wall bearing cone
JP4040556B2 (en) * 2003-09-04 2008-01-30 株式会社日立製作所 Gas turbine equipment and cooling air supply method
US6983608B2 (en) * 2003-12-22 2006-01-10 General Electric Company Methods and apparatus for assembling gas turbine engines
US8257025B2 (en) * 2008-04-21 2012-09-04 Siemens Energy, Inc. Combustion turbine including a diffuser section with cooling fluid passageways and associated methods
US8668449B2 (en) * 2009-06-02 2014-03-11 Siemens Energy, Inc. Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow
US8647057B2 (en) * 2009-06-02 2014-02-11 Siemens Energy, Inc. Turbine exhaust diffuser with a gas jet producing a coanda effect flow control
US8328518B2 (en) * 2009-08-13 2012-12-11 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels
JP4958967B2 (en) * 2009-12-15 2012-06-20 川崎重工業株式会社 Gas turbine engine with improved ventilation structure
US20130174534A1 (en) * 2012-01-05 2013-07-11 General Electric Company System and device for controlling fluid flow through a gas turbine exhaust

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2744722A (en) * 1951-04-06 1956-05-08 Gen Motors Corp Turbine bearing support

Also Published As

Publication number Publication date
US20140373504A1 (en) 2014-12-25
JP2015508860A (en) 2015-03-23
WO2013127553A1 (en) 2013-09-06
CN104145089A (en) 2014-11-12
KR20140127291A (en) 2014-11-03
IN2014DN06201A (en) 2015-10-23
CN104145089B (en) 2016-03-02
EP2634381A1 (en) 2013-09-04

Similar Documents

Publication Publication Date Title
WO2013127553A1 (en) Gas turbine having an exhaust gas diffuser and supporting fins
DE60309272T2 (en) Diffuser with boundary layer injection for a combustion chamber inlet
DE102011052236A1 (en) Profiled axial-radial outlet diffuser
CN101008351B (en) Method and apparatus for enabling engine turn down
EP2676023B1 (en) Process for cooling the turbine stage of a gas turbine
DE112012002692B4 (en) Apparatus and method for reducing air mass flow for low emission combustion over an extended range in single spool gas turbines
CH701803A1 (en) Gas turbine group and method for operating such a gas turbine group.
CH701293B1 (en) Fuel nozzle with a swirler and a plurality of vanes and gas turbine engine.
EP0799973A1 (en) Wall contour for an axial turbomachine
CN107084004A (en) Impact opening for turbine engine components
CA2567940A1 (en) Methods and apparatuses for gas turbine engines
CH701773A2 (en) Burner with radial inlet guide vanes.
EP3064706A1 (en) Guide blade assembly for a flow engine with axial flow
DE102014107020A1 (en) Diffuser strut fairing
DE102014114244A1 (en) Gas turbine blade with improved cooling
DE102011052672A1 (en) Peak flow path profile
CH703666B1 (en) Device with a turbine, a diffuser and a hub flow path profile.
CH709047A2 (en) Turbine blade and method for cooling a turbine blade of a gas turbine.
WO2016001002A1 (en) Discharge region of a turbocharger turbine
US20140161603A1 (en) Exhaust diffuser
EP2532898A1 (en) Axial turbo compressor
EP2665896A1 (en) Intermediate housing of a gas turbine with an outer bounding wall, having upstream of a supporting rib a contour that changes in the circumferential direction, for reducing secondary flow losses
CH703865A2 (en) Combustor and methods for their operation.
EP2987967B1 (en) Compressor housing for a gas turbine
EP2634382A1 (en) Gas turbine with an exhaust gas diffuser and method for operating such a gas 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: 20140717

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL 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 RS SE SI SK SM TR

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

Effective date: 20151222

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20160702