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EP2260181B1 - Guide blade having hooked fastener for a gas turbine - Google Patents

Guide blade having hooked fastener for a gas turbine Download PDF

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Publication number
EP2260181B1
EP2260181B1 EP09721575.0A EP09721575A EP2260181B1 EP 2260181 B1 EP2260181 B1 EP 2260181B1 EP 09721575 A EP09721575 A EP 09721575A EP 2260181 B1 EP2260181 B1 EP 2260181B1
Authority
EP
European Patent Office
Prior art keywords
cover plate
gas turbine
guide vane
rear edge
vane
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.)
Active
Application number
EP09721575.0A
Other languages
German (de)
French (fr)
Other versions
EP2260181A1 (en
Inventor
Igor Tsypkaykin
Beat Von Arx
Christoph Nagler
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
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
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Publication of EP2260181A1 publication Critical patent/EP2260181A1/en
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Publication of EP2260181B1 publication Critical patent/EP2260181B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to the field of gas turbines. It relates to a guide vane for a gas turbine according to the preamble of claim 1.
  • Gas turbines with sequential combustion are known and have proven themselves in industrial use.
  • Such a gas turbine which has become known in the art as GT24 / 26, for example, from an article of Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gas Turbine Family", IGTI / ASME 98-GT-220, 1998 Sweden ,
  • the local Fig. 1 shows the basic structure of such a gas turbine, where the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine goes out EP-B1-0 620 362 out.
  • the vanes 10 of Fig. 1 have a longitudinally extending airfoil 11, which in the flow direction of the hot gas (parallel arrows in Fig. 1 ) is bounded by a leading edge 14 and a trailing edge 15.
  • the blade 11 is bounded by a blade head 13 and an outer cover plate 12 (sometimes also referred to as shroud, this element being referred to below as the cover plate only).
  • the blade head 13 defines the annular hot gas channel of the turbine on the inside and usually abuts on the rotor shaft of the turbine via a seal segment not shown in detail.
  • the cover plate 12 defines with its inner side 19 the hot gas channel to the outside.
  • a front and rear hook-shaped fastening element 16 and 17 are formed, which serve on the one hand for fastening the guide vane 10 on the inner housing of the turbine and on the other hand to Absorption and fixation of heat shields adjacent to each other in the flow direction ("heat shields" Fig. 2 , Pos. 24) are available.
  • a receiving groove 18 is provided on the rear fastening element 17, in which a heat recovery segment can be inserted.
  • the receiving groove 18 is limited to the cover plate 12 through a horizontal base surface 18 ', which together with the oblique inner side 19 of this cover plate 12 in the region of the trailing edge 15 forms a wedge-shaped portion 19', which is characterized by a large volume of material.
  • the transition 21 between the trailing edge 15 of the vane 10 and the cover plate 12 is a critical range for the life of the vane 10, since it sets a high thermal load resulting from a thermal-mechanical mismatch between the cover plate 12 and the blade 11 This results in a peak being superimposed on the stress resulting from the load of the airfoil 11 loaded by the hot gas flow.
  • the above-mentioned large volume of material in the wedge-shaped portion 19 'above the trailing edge 15 now leads to a significant increase in the thermal stresses in this important for the life of the vane 10 area and thus to a reduction in the life itself, bearing in mind the fact that modern gas turbines high Require temperatures related to the working fluids, which are in many cases beyond the permissible material temperature economically useful materials.
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a guide vane for gas turbines, which avoids the disadvantages of the previous vanes with extremely small and targeted changes in the design and is characterized by a significantly improved life.
  • the object is solved by the entirety of the features of claim 1.
  • Essential to the invention is that means are provided on the cover plate of the guide vane between the receiving groove and the trailing edge, which ensure a reduction of the thermal and mechanical stresses in the region of the transition between the trailing edge and cover plate. As a result of this engagement directly on the cover plate in the region of the trailing edge, the thermal and mechanical loads with regard to the service life of the blade can be sustainably improved there in a very simple and efficient manner.
  • the cover plate has a reduced material thickness in the region between the trailing edge and the receiving groove. This material reduction effectively minimizes the stresses caused by thermal and mechanical stresses in this area.
  • the means for reducing the thermal and mechanical stresses preferably comprise a groove formed between receiving groove and trailing edge in the cover plate, which groove is arranged substantially parallel to the inside of the cover plate and directed counter to the flow direction.
  • the trailing edge of the blade is formed opposite to the fastening element in the flow direction set back by a distance.
  • the vane of the invention can be used to advantage in a gas turbine.
  • FIGS. 2 and 3 is in one too Fig. 1 comparable representation of a guide vane according to an embodiment of the invention.
  • the guide vane 20 in turn comprises an airfoil 11 with leading edge 14 and trailing edge 15 which is delimited in the longitudinal direction by a vane head 13 and a cover plate 12.
  • the cover plate 12 also here has an obliquely outwardly inclined inside in the flow direction 19.
  • hook-shaped fasteners 16 and 17 are formed, wherein the Rear fastening element 17 is formed on the rear side of a receiving groove 22 for an adjacent heat spreader 24.

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

Description

Technisches GebietTechnical area

Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinen. Sie betrifft eine Leitschaufel für eine Gasturbine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbines. It relates to a guide vane for a gas turbine according to the preamble of claim 1.

Stand der TechnikState of the art

Gasturbinen mit sequentieller Verbrennung sind bekannt und haben sich im industriellen Einsatz bewährt.
Eine solche Gasturbine, welche in Fachkreisen als GT24/26 bekannt geworden ist, geht beispielsweise aus einem Aufsatz von Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24/GT26 Gasturbine Family", IGTI/ASME 98-GT-220, 1998 Stockholm . Die dortige Fig. 1 zeigt den grundsätzlichen Aufbau einer solchen Gasturbine, wobei die dortige Fig. 1 in der vorliegenden Anmeldung als Fig. 1 wiedergegeben ist. Des Weiteren geht eine solche Gasturbine aus EP-B1-0 620 362 hervor.Gas turbines with sequential combustion are known and have proven themselves in industrial use.
Such a gas turbine, which has become known in the art as GT24 / 26, for example, from an article of Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gas Turbine Family", IGTI / ASME 98-GT-220, 1998 Stockholm , The local Fig. 1 shows the basic structure of such a gas turbine, where the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine goes out EP-B1-0 620 362 out.

Die Leitschaufeln 10 der Fig. 1 haben ein sich in Längsrichtung erstreckendes Schaufelblatt 11, das in Strömungsrichtung des Heissgases (parallele Pfeile in Fig. 1) von einer Vorderkante 14 und einer Hinterkante 15 begrenzt ist. In der Längsrichtung wird das Schaufelblatt 11 von einem Schaufelkopf 13 und einer äusseren Deckplatte 12 (bisweilen auch Deckband genannt, wobei dieses Element im folgenden nur noch Deckplatte genannt wird) begrenzt. Der Schaufelkopf 13 begrenzt den ringförmigen Heissgaskanal der Turbine auf der Innenseite und stösst ublicherweise über ein nicht näher gezeigtes Dichtungssegment an die Rotorwelle der Turbine an. Die Deckplatte12 begrenzt mit ihrer Innenseite 19 den Heissgaskanal nach aussen.The vanes 10 of Fig. 1 have a longitudinally extending airfoil 11, which in the flow direction of the hot gas (parallel arrows in Fig. 1 ) is bounded by a leading edge 14 and a trailing edge 15. In the longitudinal direction, the blade 11 is bounded by a blade head 13 and an outer cover plate 12 (sometimes also referred to as shroud, this element being referred to below as the cover plate only). The blade head 13 defines the annular hot gas channel of the turbine on the inside and usually abuts on the rotor shaft of the turbine via a seal segment not shown in detail. The cover plate 12 defines with its inner side 19 the hot gas channel to the outside.

An der Aussenseite der Deckplatte 12, die mit einem Kühlmedium (z. B. Kühlluft) durchströmt ist, sind ein vorderes und hinteres hakenförmiges Befestigungselement 16 bzw. 17 angeformt, die einerseits zur Befestigung der Leitschaufel 10 am inneren Gehäuse der Turbine dienen und andererseits zur Aufnahme und Fixierung von in Strömungsrichtung benachbarten Wärmestausegmenten ("heat shields". Siehe Fig. 2, Pos. 24) zur Verfügung stehen. Hierzu ist am hinteren Befestigungselement 17 eine Aufnahmenut 18 vorgesehen, in die ein Wärmestausegment eingeschoben werden kann. Die Aufnahmenut 18 ist zur Deckplatte 12 hin durch eine horizontale Grundfläche 18' begrenzt, die zusammen mit der schrägen Innenseite 19 dieser Deckplatte 12 im Bereich der Hinterkante 15 einen keilförmigen Abschnitt 19' bildet, der durch ein grosses Materialvolumen charakterisiert ist.On the outside of the cover plate 12, which is flowed through by a cooling medium (eg., Cooling air), a front and rear hook-shaped fastening element 16 and 17 are formed, which serve on the one hand for fastening the guide vane 10 on the inner housing of the turbine and on the other hand to Absorption and fixation of heat shields adjacent to each other in the flow direction ("heat shields" Fig. 2 , Pos. 24) are available. For this purpose, a receiving groove 18 is provided on the rear fastening element 17, in which a heat recovery segment can be inserted. The receiving groove 18 is limited to the cover plate 12 through a horizontal base surface 18 ', which together with the oblique inner side 19 of this cover plate 12 in the region of the trailing edge 15 forms a wedge-shaped portion 19', which is characterized by a large volume of material.

Der Übergang 21 zwischen der Hinterkante 15 der Leitschaufel 10 und der Deckplatte 12 stellt einen kritischen Bereich für die Lebensdauer der Leitschaufel 10 dar, da sich in ihm eine hohe thermische Belastung einstellt, die sich aus einer thermisch-mechanischen Fehlanpassung zwischen Deckplatte 12 und Schaufelblatt 11 ergibt, wobei dies dazu führt, dass eine Spitze in der mechanischen Spannung, welche aus der Belastung des durch die Heissgasströmung beaufschlagten Schaufelblattes 11 resultiert, überlagert wird. Das oben erwähnte grosse Materialvolumen im keilförmigen Abschnitt 19' oberhalb der Hinterkante 15 führt nun zu einem deutlichen Anstieg der thermischen Spannungen in diesem für die Lebensdauer der Leitschaufel 10 wichtigen Bereich und damit zu einer Verringerung der Lebensdauer selbst, eingedenk der Tatsache, dass moderne Gasturbinen hohe Temperaturen betreffend die Arbeitsfluide erfordern, die in vielen Fällen jenseits der zulässigen Materialtemperatur wirtschaftlich einsetzbarer Werkstoffe liegen.The transition 21 between the trailing edge 15 of the vane 10 and the cover plate 12 is a critical range for the life of the vane 10, since it sets a high thermal load resulting from a thermal-mechanical mismatch between the cover plate 12 and the blade 11 This results in a peak being superimposed on the stress resulting from the load of the airfoil 11 loaded by the hot gas flow. The above-mentioned large volume of material in the wedge-shaped portion 19 'above the trailing edge 15 now leads to a significant increase in the thermal stresses in this important for the life of the vane 10 area and thus to a reduction in the life itself, bearing in mind the fact that modern gas turbines high Require temperatures related to the working fluids, which are in many cases beyond the permissible material temperature economically useful materials.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Es ist daher Aufgabe der Erfindung, eine Leitschaufel für Gasturbinen zu schaffen, welche mit äusserst geringen und gezielten Änderungen im Design die geschilderten Nachteile der bisherigen Leitschaufeln vermeidet und sich durch eine deutlich verbesserte Lebensdauer auszeichnet.The invention aims to remedy this situation. It is therefore an object of the invention to provide a guide vane for gas turbines, which avoids the disadvantages of the previous vanes with extremely small and targeted changes in the design and is characterized by a significantly improved life.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Wesentlich für die Erfindung ist, dass an der Deckplatte der Leitschaufel zwischen der Aufnahmenut und der Hinterkante Mittel vorgesehen sind, welche eine Reduzierung der thermischen und mechanischen Spannungen im Bereich des Übergangs zwischen Hinterkante und Deckplattegewährleisten. Durch diesen Eingriff direkt an der Deckplatte im Bereich der Hinterkante können dort auf sehr einfache und effiziente Weise die thermischen und mechanischen Belastungen im Hinblick auf die Lebensdauer der Schaufel nachhaltig verbessert werden.The object is solved by the entirety of the features of claim 1. Essential to the invention is that means are provided on the cover plate of the guide vane between the receiving groove and the trailing edge, which ensure a reduction of the thermal and mechanical stresses in the region of the transition between the trailing edge and cover plate. As a result of this engagement directly on the cover plate in the region of the trailing edge, the thermal and mechanical loads with regard to the service life of the blade can be sustainably improved there in a very simple and efficient manner.

Gemäss einer Ausgestaltung der Erfindung weist die Deckplatte im Bereich zwischen Hinterkante und Aufnahmenut eine reduzierte Materialstärke auf. Durch diese Materialreduktion können wirkungsvoll die durch thermische und mechanische Spannungen hervorgerufenen Belastungen in diesem Bereich minimiert werden.According to one embodiment of the invention, the cover plate has a reduced material thickness in the region between the trailing edge and the receiving groove. This material reduction effectively minimizes the stresses caused by thermal and mechanical stresses in this area.

Vorzugsweise umfassen die Mittel zur Reduzierung der thermischen und mechanischen Spannungen eine zwischen Aufnahmenut und Hinterkante in die Deckplatte eingebrachte Hohlkehle, die im wesentlichen parallel zur Innenseite der Deckplatte angeordnet und entgegen der Strömungsrichtung gerichtet ist.The means for reducing the thermal and mechanical stresses preferably comprise a groove formed between receiving groove and trailing edge in the cover plate, which groove is arranged substantially parallel to the inside of the cover plate and directed counter to the flow direction.

Darüber hinaus ist es von Vorteil, wenn die Hinterkante der Schaufel gegenüber dem Befestigungselement in Strömungsrichtung um einen Abstand zurückversetzt ausgebildet ist.Moreover, it is advantageous if the trailing edge of the blade is formed opposite to the fastening element in the flow direction set back by a distance.

Die Leitschaufel nach der Erfindung kann mit Vorteil in einer Gasturbine eingesetzt werden.The vane of the invention can be used to advantage in a gas turbine.

Kurze Erläuterung der FigurenBrief explanation of the figures

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Alle für das unmittelbare Verständnis der Erfindung unwesentlichen Elemente sind fortgelassen worden. Gleiche Elemente sind in den verschiedenen Figuren mit den gleichen Bezugszeichen versehen. Die Strömungsrichtung der Medien ist mit Pfeilen angegeben. Es zeigen

Fig. 1
in einer Seitenansicht eine Leitschaufel, wie sie bisher in Gasturbinen eingebaut worden ist;
Fig. 2
in einer zu Fig. 1 vergleichbaren Darstellung eine Leitschaufel gemäss einem Ausführungsbeispiel der Erfindung und
Fig. 3
einen vergrösserten Ausschnitt aus Fig. 2 mit dem Übergang von der Hinterkante des Schaufelblattes zum hinteren Befestigungselement der Leitschaufel.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. All elements which are immaterial to the immediate understanding of the invention have been omitted. The same elements are provided in the various figures with the same reference numerals. The flow direction of the media is indicated by arrows. Show it
Fig. 1
in a side view of a guide vane, as has been installed in gas turbines so far;
Fig. 2
in one too Fig. 1 Comparative illustration of a guide vane according to an embodiment of the invention and
Fig. 3
an enlarged section Fig. 2 with the transition from the trailing edge of the airfoil to the rear fastener of the vane.

Wege zur Ausführung der ErfindungWays to carry out the invention

In Fig. 2 und 3 ist in einer zu Fig. 1 vergleichbaren Darstellung eine Leitschaufel gemäss einem Ausführungsbeispiel der Erfindung dargestellt. Die Leitschaufel 20 umfasst wiederum ein Schaufelblatt 11 mit Vorderkante 14 und Hinterkante 15, das in Längsrichtung von einem Schaufelkopf 13 und einer Deckplatte 12 begrenzt ist. Die Deckplatte 12 hat auch hier eine in Strömungsrichtung schräg nach aussen geneigte Innenseite 19. Auf der Aussenseite der Deckplatte 12 sind wiederum hakenförmige Befestigungselemente 16 und 17 ausgebildet, wobei am hinteren Befestigungselement 17 auf der hinteren Seite eine Aufnahmenut 22 für ein angrenzendes Wärmestausegment 24 ausgebildet ist.In FIGS. 2 and 3 is in one too Fig. 1 comparable representation of a guide vane according to an embodiment of the invention. The guide vane 20 in turn comprises an airfoil 11 with leading edge 14 and trailing edge 15 which is delimited in the longitudinal direction by a vane head 13 and a cover plate 12. The cover plate 12 also here has an obliquely outwardly inclined inside in the flow direction 19. On the outside of the cover plate 12 turn hook-shaped fasteners 16 and 17 are formed, wherein the Rear fastening element 17 is formed on the rear side of a receiving groove 22 for an adjacent heat spreader 24.

Zur Verringerung der thermischen und mechanischen Spannungen zwischen der Hinterkante 15 des Schaufelblattes 11 und der Deckplatte 12 ist nun unterhalb der Aufnahmenut 22 eine im wesentlichen parallel zur Innenseite 19 verlaufende Hohlkehle 23 vorgesehen, die zu einer deutlichen Reduktion der Dicke und damit des Materialvolumens der Deckplatte 12 im Bereich oberhalb der Hinterkante 15 führt. Gleichzeitig ist die Hinterkante 15 in Strömungsrichtung gegenüber dem hinteren Befestigungselement 17 mit einem Abstand a (Fig. 3) nach hinten versetzt wodurch eine weitere thermische und mechanische Entkopplung erreicht wird.To reduce the thermal and mechanical stresses between the trailing edge 15 of the blade 11 and the cover plate 12 is now below the receiving groove 22 a substantially parallel to the inner side 19 extending groove 23 is provided, which leads to a significant reduction in the thickness and thus the material volume of the cover plate 12th in the area above the trailing edge 15 leads. At the same time, the trailing edge 15 in the flow direction opposite to the rear fastening element 17 is at a distance a (FIG. Fig. 3 ) offset backwards whereby a further thermal and mechanical decoupling is achieved.

Insgesamt kann die Lösung gemäss der Erfindung wie folgt charakterisiert werden:

  • Eine Hohlkehle 23, die in ihrer Form hinsichtlich der thermisch-mechanischen Anpassung zwischen der Deckplatte 12 und der Hinterkante 15 optimiert ist, reduziert das Materialvolumen oberhalb der Hinterkante 15.
  • Die Hohlkehle 23 ist unterhalb der Aufnahmenut 22 angeordnet.
  • Die Hinterkante 15 ist gegenüber dem Befestigungselement 17 zurückversetzt, um die thermische Spannung an dem kritischen Übergang zwischen Hinterkante und Deckplatte 12 zu reduzieren.
  • Die Hohlkehle 23 wird so dimensioniert, dass die Reduktion des Materialvolumen oberhalb der Hinterkante 15 keine Festigkeitseinbusse am bestimmungsgemässen Gebrauch der Schaufel nach sich zieht.
Overall, the solution according to the invention can be characterized as follows:
  • A groove 23, which is optimized in shape with respect to the thermo-mechanical adaptation between the cover plate 12 and the trailing edge 15, reduces the material volume above the trailing edge 15.
  • The groove 23 is arranged below the receiving groove 22.
  • The trailing edge 15 is set back relative to the fastening element 17 in order to reduce the thermal stress at the critical transition between the trailing edge and the cover plate 12.
  • The groove 23 is dimensioned so that the reduction of the volume of material above the trailing edge 15 does not result in a loss of strength due to the intended use of the blade.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

10,2010.20
Leitschaufel (Gasturbine)Guide vane (gas turbine)
1111
Schaufelblattairfoil
1212
Deckplattecover plate
1313
Schaufelkopfshovel head
1414
Vorderkanteleading edge
1515
Hinterkantetrailing edge
16,1716.17
Befestigungselement (hakenförmig)Fastening element (hook-shaped)
18,2218.22
Aufnahmenut (Wärmestausegment)Receiving groove (heat recovery segment)
18'18 '
Grundfläche (Aufnahmenut)Base (receiving groove)
1919
Innenseite (äussere Plattform)Inside (outer platform)
19'19 '
Keilförmiger AbschnittWedge-shaped section
2121
Übergang (Hinterkante-äussere Plattform)Transition (trailing edge outer platform)
2323
Hohlkehlefillet
2424
WärmestausegmentHeat shield
2525
Heissgashot gas
aa
Abstanddistance

Claims (3)

  1. Guide vane (20) for a gas turbine, which guide vane (20) comprises a vane blade (11) which extends in the vane longitudinal direction and is delimited by a front edge (14) and a rear edge (15), and a cover plate (12), the inside (19) of which is exposed to the hot gas flowing through the gas turbine and on which at least one hooked fastener (17) is provided protruding outward in the region of the rear edge for fastening the guide vane (20) to a housing or to elements of the gas turbine, wherein above the rear edge (15), the hooked fastener (17) has at least one receiving groove (22) for fixing a heat accumulation segment (24) adjoining the outer cover plate (12) of the guide vane (20) in the flow direction of the hot gas, characterized in that a hollow fillet (23) is provided on the cover plate (12) of the guide vane (20) between the receiving groove (22) and the rear edge (15) of the vane blade (11) against the flow direction, for reducing the thermal and mechanical strains in the area of the transition (21) between the rear edge (15) and the cover plate (12), that the cover plate (12) has a reduced thickness in the region between the rear edge (15) and the receiving groove (22), that the course of the hollow fillet (23) is formed substantially parallel to the inside (19) of the cover plate (12), and that the rear edge (15) is offset to the rear in the flow direction by a distance (a) relative to the fastener (17).
  2. Use of the guide vane (20) according to claim 1 for a gas turbine.
  3. Use of the guide vane (20) according to claim 2 for a gas turbine with sequential combustion.
EP09721575.0A 2008-03-19 2009-02-18 Guide blade having hooked fastener for a gas turbine Active EP2260181B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4162008 2008-03-19
PCT/EP2009/051883 WO2009115384A1 (en) 2008-03-19 2009-02-18 Guide blade having hooked fastener for a gas turbine

Publications (2)

Publication Number Publication Date
EP2260181A1 EP2260181A1 (en) 2010-12-15
EP2260181B1 true EP2260181B1 (en) 2016-08-17

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EP (1) EP2260181B1 (en)
WO (1) WO2009115384A1 (en)

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DE102004004014A1 (en) * 2004-01-27 2005-08-18 Mtu Aero Engines Gmbh Stator blade for turbomachines has in its outer cover strip a recess adjacent to flow outlet edge or rear edge of blade to reduce material thickness in this area
FR2896548B1 (en) * 2006-01-24 2011-05-27 Snecma SECTORIZED FIXED RECTIFIER ASSEMBLY FOR A TURBOMACHINE COMPRESSOR
US7862300B2 (en) * 2006-05-18 2011-01-04 Wood Group Heavy Industrial Turbines Ag Turbomachinery blade having a platform relief hole

Also Published As

Publication number Publication date
US8147190B2 (en) 2012-04-03
US20110016875A1 (en) 2011-01-27
EP2260181A1 (en) 2010-12-15
WO2009115384A1 (en) 2009-09-24

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