EP2414640B1 - Blade for a gas turbine - Google Patents

Blade for a gas turbine Download PDF

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Publication number
EP2414640B1
EP2414640B1 EP10706671.4A EP10706671A EP2414640B1 EP 2414640 B1 EP2414640 B1 EP 2414640B1 EP 10706671 A EP10706671 A EP 10706671A EP 2414640 B1 EP2414640 B1 EP 2414640B1
Authority
EP
European Patent Office
Prior art keywords
cooling
cover strip
side rails
blade according
segment
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.)
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Application number
EP10706671.4A
Other languages
German (de)
French (fr)
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EP2414640A1 (en
Inventor
Chiara Zambetti
Sergei Riazantsev
Héléne SAXER-FELICI
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
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Ansaldo Energia IP UK Ltd
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Publication of EP2414640A1 publication Critical patent/EP2414640A1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a blade for a gas turbine according to the preamble of claim 1.
  • a gas turbine blade which is equipped with a shroud segment at the blade tip.
  • the cover band segments of the blades of a row of blades together form a circumferential cover band.
  • the shroud segments are provided with upwardly projecting side rails running along the side edges, which improve the tightness of the shroud against the hot gas duct of the turbine. No statement is made about the cooling of the shroud segments or the shroud.
  • a turbine blade arrangement with a shroud in which the shroud segments are equipped with a circumferential sealing rib, in which a circumferential slot is also provided.
  • An air flow supplied in the bottom area of the slot exits at the upper edge of the sealing rib and mixes with a leakage air flow in the gap between the upper edge and the adjacent duct wall.
  • the air stream fed into the slot can be obtained from a cooling air stream that is guided through the shroud segment.
  • a turbine blade with an actively cooled shroud segment has become known.
  • a plurality of cooling ducts is provided in the shroud segment, which, starting from a type of main cooling air duct arranged centrally in the shroud segment, extend in the circumferential direction, ie in the direction of the adjacent shroud segment.
  • One embodiment shows cooling channels which end in surface recesses which are open to the outside and which run parallel to the side edges.
  • recesses are provided in the side edges, so that there is a gap between two shroud segments in which the cooling air ducts end. The cooling air flow entering the gap is divided into two air flows, one of which cools the top and one the bottom of the shroud segments.
  • the invention seeks to remedy this. It is therefore an object of the invention to provide a gas turbine blade with a cooled shroud segment in which the cooling of the side rails is maximized.
  • this is preferably achieved in that a plurality of cooling tubes extending transversely to the side rails are arranged on the upper side of the shroud segment, which start from a central piece arranged between the side rails and from which cooling air can be applied, and which into the Side rails end and connect to the slots in the side rails.
  • Another embodiment of the invention is characterized in that the middle piece is arranged in the middle between the side rails.
  • the middle piece can also be arranged offset to the middle between the side rails.
  • the cooling tubes run parallel to one another, with the center piece extends substantially parallel to the side rails.
  • the cooling tubes can run in the circumferential direction of the shroud. However, it is also conceivable that the cooling tubes run obliquely to the circumferential direction of the shroud.
  • cooling tubes each have a cooling hole and are designed for convective cooling of the shroud segment, and that the cooling tubes are molded on the shroud segment.
  • a further embodiment of the invention is characterized in that the cooling tubes of vanes adjoining one another with the shroud segments are arranged on a gap.
  • the shroud segment is delimited in the axial direction by wall segments which extend in the circumferential direction, the cooling air emerging from the slots being supplied via cooling bores in the region of the wall segments and the side rails.
  • a further embodiment is characterized in that the shroud segment is delimited in the axial direction by wall segments extending in the circumferential direction, that an intermediate wall segment is provided parallel to the wall segments and that between the intermediate wall segment and the wall segments in the A slot is provided for each side rail.
  • the slots of a side rail can each be connected to one another by a cooling hole running in the side rail.
  • film cooling bores extend from the cooling bores supplying the slots and open into the hot gas channel on the underside of the shroud segment.
  • the approximately rectangular shroud segment 12 'in the example shown in the base area is delimited on two opposite sides by comparatively high wall segments 14 and 15 which, together with the wall segments of the other blades of a complete row of blades, form annular circumferential walls between which a shroud cavity is formed which against the penetration of hot gas from the hot gas duct underneath is sealed.
  • comparatively high wall segments 14 and 15 which, together with the wall segments of the other blades of a complete row of blades, form annular circumferential walls between which a shroud cavity is formed which against the penetration of hot gas from the hot gas duct underneath is sealed.
  • parallel, upwardly projecting side rails 16, 17 are formed, with which adjacent shroud segments of the row of blades abut one another.
  • a rib-like, internally hollow center piece 13 is arranged parallel to it, which is connected to the cooling air channels running in the radial direction inside the airfoil 11.
  • cooling tubes 18, which are molded onto the side rails 16, 17 extend transversely to the side rails 16, 17 on both sides of the center piece on the upper side of the shroud segment 12 ' to and end at a distance in front of the side rails 16, 17.
  • four parallel cooling tubes 18 are provided on both sides of the center piece 13, which run parallel or quasi-parallel to the wall segments 14, 15. However, they can also be oriented at an angle to the wall segments 14, 15 ( Fig. 2 ).
  • an intermediate space 22 is created.
  • the cooling air flows out into this intermediate space 22, which flows through the cooling bores 21 in the interior of the cooling tubes 18 and thus convectively cools the shroud segment 12 '.
  • the cooling air flowing through the cooling pipes 18 comes from the cooling air supply 20 in the interior of the middle piece 13, with which the cooling bores 21 are connected and into which a cooling air flow 25 enters from below.
  • FIG. 3 and 6 are in one too Fig. 1 or 4 comparable representation of the blade tip of a gas turbine blade provided with a shroud segment according to a preferred exemplary embodiment of the invention and the section through the shroud segment of the blade Fig. 3 reproduced in the level VI-VI.
  • the cover band segment 12 of the blade 10 Fig. 3 and 6 is different from the previous solution Fig. 1 and 4th designed so that the side rails 16, 17 are now also convectively cooled.
  • the cooling pipes 18 are now led directly to the side rails 16, 17, giving up the intermediate space.
  • These slots can also be arranged quasi-parallel to the rail, which also applies to the slots 23.1, 23.2 Fig. 13 applies.
  • the cooling air flowing through the cooling bores 21 exits into the slots 23, 24 and from there into the shroud cavity.
  • the side rails 16, 17 are also convectively cooled along the length of the slots 23, 24, without the need for an additional cooling air mass flow which impairs the effectiveness of the turbine.
  • the distributed cooling tubes 18 ensure that the slots 23, 24 are supplied with cooling air evenly over their entire length.
  • the cooling tubes 18 are in the Fig. 3 6 or 6 shown embodiment formed on the top of the shroud segment 12 (when the blade 10 is being cast) and thus have a close thermal coupling to the body of the shroud segment 12.
  • the cooling bores 21 are introduced into the cooling tubes 18 from the outside, and again towards the outside be closed.
  • the cooling tubes 18 can run parallel to the wall segments 14, 15, as shown in FIG Fig. 3 is shown. But you can also according to Fig. 2 be oriented obliquely to the wall segments 14, 15. Likewise, the middle piece - as in Fig. 6 shown - be located exactly in the middle between the wall segments 14, 15. But it can also be analogous to Fig. 5 be offset from the center.
  • a strip-shaped seal 26 is inserted between the abutting cover band segments of adjacent blades 10a and 10b with their cooling bores 21a and 21b and their slots 24a and 23b, which prevents or impedes the penetration of the hot gases from the hot gas channel into the cover band cavity.
  • cooling bores 27, 28 can be provided in the wall segments 14, 15 or the side rails 16, 17 (see also Fig. 8 ) be introduced, through the cooling air to the slots and at the same time still convective cooling of the thickened cover band areas. From these cooling holes - as in Fig. 11 shown - go off film cooling bores 30, which open into the hot gas channel lying below the shroud segment and there cause film cooling of the underside of the shroud. This applies according to Fig. 12 also for the cooling bores 21.
  • a cooling bore 28 running in the side rails 16, 17 can according to Fig. 13 also connect two separate slots 23.1 and 23.2 to one another if the shroud segment is provided with an intermediate wall segment 31 arranged in parallel between the wall segments 14, 15.
  • an enlarged groove-shaped space 29 is provided, which is filled with cooling air from the cooling bores 21a, 21b and thus prevents the penetration of hot gases.
  • the cooling tubes 18a, 18b are then in accordance with FIG Fig. 9 "on gap" are arranged opposite the adjacent blade.

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

Description

Technisches GebietTechnical field

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

Stand der TechnikState of the art

Aus der EP-A1-1591 625 ist eine Gasturbinenschaufel bekannt, die an der Schaufelspitze mit einem Deckbandsegment ausgestattet ist. Die Deckbandsegmente der Schaufeln einer Schaufelreihe bilden zusammen ein umlaufendes Deckband. An den Seitenkanten, an denen die benachbarten Deckbandsegmente eines Deckbandes zusammenstossen, sind die Deckbandsegmente mit an den Seitenkanten entlang laufenden, nach oben abstehenden Seitenschienen versehen, welche die Dichtigkeit des Deckbandes gegenüber dem Heissgaskanal der Turbine verbessern. Über die Kühlung der Deckbandsegmente bzw. des Deckbandes wird keine Aussage gemacht.From the EP-A1-1591 625 a gas turbine blade is known which is equipped with a shroud segment at the blade tip. The cover band segments of the blades of a row of blades together form a circumferential cover band. At the side edges at which the adjacent shroud segments of a shroud collide, the shroud segments are provided with upwardly projecting side rails running along the side edges, which improve the tightness of the shroud against the hot gas duct of the turbine. No statement is made about the cooling of the shroud segments or the shroud.

Aus der DE-A1-196 01 818 ist eine Turbinenschaufelanordnung mit einem Deckband bekannt, bei dem die Deckbandsegmente mit einer umlaufenden Dichtrippe ausgestattet sind, in der ein ebenfalls umlaufender Schlitz vorgesehen ist. Ein im Bodenbereich des Schlitzes dort zugeführter Luftstrom tritt an der Oberkante der Dichtrippe aus und vermischt sich im Spalt zwischen Oberkante und angrenzender Kanalwand mit einem Leckage-Luftstrom. Der in den Schlitz zugeführte Luftstrom kann dabei aus einem Kühlluftstrom gewonnen werden, der durch das Deckbandsegment geführt wird. Im Zentrum der Überlegung steht hier indessen die Reduzierung der Leckageverluste, nicht jedoch die Kühlung des Deckbandsegments.From the DE-A1-196 01 818 a turbine blade arrangement with a shroud is known, in which the shroud segments are equipped with a circumferential sealing rib, in which a circumferential slot is also provided. An air flow supplied in the bottom area of the slot exits at the upper edge of the sealing rib and mixes with a leakage air flow in the gap between the upper edge and the adjacent duct wall. The air stream fed into the slot can be obtained from a cooling air stream that is guided through the shroud segment. At the center of the consideration is here however, the reduction in leakage losses, but not the cooling of the shroud segment.

Aus der EP 1 013 884 A2 ist eine Turbinenschaufel mit einem aktiv gekühlten Deckbandsegment bekannt geworden. Hierzu ist im Deckbandsegment eine Vielzahl von Kühlkanälen vorgesehen, die ausgehend von einer Art mittig im Deckbandsegment angeordneten Hauptkühlluftkanal sich in Umlaufrichtung, d.h. in Richtung des benachbarten Deckbandsegmentes, erstrecken. Eine Ausführungsform zeigt Kühlkanäle, die in zum Aussenraum offenen Oberflächenvertiefungen enden, die parallel zu den Seitenkanten verlaufen. In einer anderen Ausführungsform sind in den Seitenkanten Ausnehmungen vorgesehen, so dass sich zwischen zwei Deckbandsegmenten ein Spalt befindet, in dem die Kühlluftkanäle enden. Der in dem Spalt eintretende Kühlluftstrom teilt sich in zwei Luftströme auf, von dem einer die Oberseite und einer die Unterseite der Deckbandsegmente kühlt. Die Deckbandsegmente gemäss EP 1 013 884 A2 weisen aber keine Seitenschienen auf. Ausserdem geht aus den signifikanten Figuren 1, 3 und 5 dieser Druckschrift nicht hervor, dass Schlitze in den Seitenschienen vorhanden sind, aus welchen Kühlluft in den Deckbandhohlraum austritt.From the EP 1 013 884 A2 a turbine blade with an actively cooled shroud segment has become known. For this purpose, a plurality of cooling ducts is provided in the shroud segment, which, starting from a type of main cooling air duct arranged centrally in the shroud segment, extend in the circumferential direction, ie in the direction of the adjacent shroud segment. One embodiment shows cooling channels which end in surface recesses which are open to the outside and which run parallel to the side edges. In another embodiment, recesses are provided in the side edges, so that there is a gap between two shroud segments in which the cooling air ducts end. The cooling air flow entering the gap is divided into two air flows, one of which cools the top and one the bottom of the shroud segments. The cover band segments according to EP 1 013 884 A2 but have no side rails. It also goes from the significant Figures 1 , 3rd and 5 this publication does not indicate that there are slots in the side rails from which cooling air exits into the shroud cavity.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Es ist daher Aufgabe der Erfindung, eine Gasturbinenschaufel mit gekühltem Deckbandsegment zu schaffen, bei der die Kühlung der Seitenschienen maximiert wird.The invention seeks to remedy this. It is therefore an object of the invention to provide a gas turbine blade with a cooled shroud segment in which the cooling of the side rails is maximized.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Wesentlich für die Erfindung ist, dass zur Verbesserung der Kühlung im Bereich der Seitenschienen in den Seitenschienen schienenparallele, nach oben offene Schlitze angeordnet sind, durch welche über das Deckbandsegment aus dem Inneren des Schaufelblattes herangeführte Kühlluft in den Raum oberhalb des Deckbandsegments austritt.The object is achieved by the entirety of the features of claim 1. It is essential for the invention that, in order to improve the cooling in the area of the side rails, slots parallel to the rails, which are open at the top, are arranged, through which cooling air coming from the interior of the airfoil via the shroud segment exits into the space above the shroud segment.

Vorzugsweise wird dies gemäss einer Ausgestaltung der Erfindung dadurch erreicht, dass auf der Oberseite des Deckbandsegments eine Mehrzahl von quer zu den Seitenschienen verlaufenden Kühlrohren angeordnet sind, welche von einem zwischen den Seitenschienen angeordneten Mittelstück ausgehen und von dort mit Kühlluft beaufschlagbar sind, und welche in den Seitenschienen enden und mit den Schlitzen in den Seitenschienen in Verbindung stehen.According to one embodiment of the invention, this is preferably achieved in that a plurality of cooling tubes extending transversely to the side rails are arranged on the upper side of the shroud segment, which start from a central piece arranged between the side rails and from which cooling air can be applied, and which into the Side rails end and connect to the slots in the side rails.

Eine andere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass das Mittelstück in der Mitte zwischen den Seitenschienen angeordnet ist. Das Mittelstück kann auch versetzt zur Mitte zwischen den Seitenschienen angeordnet sein. Insbesondere verlaufen die Kühlrohre parallel zueinander, wobei sich das Mittelstück im wesentlichen parallel zu den Seitenschienen erstreckt.Another embodiment of the invention is characterized in that the middle piece is arranged in the middle between the side rails. The middle piece can also be arranged offset to the middle between the side rails. In particular, the cooling tubes run parallel to one another, with the center piece extends substantially parallel to the side rails.

Dabei können die Kühlrohre in Umfangsrichtung des Deckbandes verlaufen. Es ist aber auch denkbar, dass die Kühlrohre schräg zur Umfangsrichtung des Deckbandes verlaufen.The cooling tubes can run in the circumferential direction of the shroud. However, it is also conceivable that the cooling tubes run obliquely to the circumferential direction of the shroud.

Eine andere Ausgestaltung der Erfindung zeichnet sich dadurch aus, dass die Kühlrohre jeweils eine Kühlbohrung aufweisen und zur konvektiven Kühlung des Deckbandsegments ausgebildet sind, und dass die Kühlrohre am Deckbandsegment angeformt sind.Another embodiment of the invention is characterized in that the cooling tubes each have a cooling hole and are designed for convective cooling of the shroud segment, and that the cooling tubes are molded on the shroud segment.

Eine weitere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die Kühlrohre von mit den Deckbandsegmenten aneinander grenzenden Schaufeln auf Lücke angeordnet sind.A further embodiment of the invention is characterized in that the cooling tubes of vanes adjoining one another with the shroud segments are arranged on a gap.

Gemäss einer anderen Ausgestaltung der Erfindung ist das Deckbandsegment in axialer Richtung durch sich in Umfangsrichtung erstreckende Wandsegmente begrenzt, wobei die aus den Schlitzen austretende Kühlluft über Kühlbohrungen im Bereich der Wandsegmente und der Seitenschienen zugeführt wird.According to another embodiment of the invention, the shroud segment is delimited in the axial direction by wall segments which extend in the circumferential direction, the cooling air emerging from the slots being supplied via cooling bores in the region of the wall segments and the side rails.

Eine weitere Ausgestaltung zeichnet sich dadurch aus, dass das Deckbandsegment in axialer Richtung durch sich in Umfangsrichtung erstreckende Wandsegmente begrenzt ist, dass parallel zu den Wandsegmenten ein in der Mitte zwischen den Wandsegmenten angeordnetes Zwischenwandsegment vorgesehen ist, und dass zwischen dem Zwischenwandsegment und den Wandsegmenten in den Seitenschienen jeweils ein Schlitz vorgesehen ist.A further embodiment is characterized in that the shroud segment is delimited in the axial direction by wall segments extending in the circumferential direction, that an intermediate wall segment is provided parallel to the wall segments and that between the intermediate wall segment and the wall segments in the A slot is provided for each side rail.

Insbesondere können die Schlitze einer Seitenschiene dabei jeweils durch eine in der Seitenschiene verlaufende Kühlbohrung miteinander verbunden sein.In particular, the slots of a side rail can each be connected to one another by a cooling hole running in the side rail.

Gemäss einer anderen Ausgestaltung gehen von den die Schlitze versorgenden Kühlbohrungen Filmkühlungsbohrungen ab und münden auf der Unterseite des Deckbandsegments in den Heissgaskanal.According to another embodiment, film cooling bores extend from the cooling bores supplying the slots and open into the hot gas channel on the underside of the shroud segment.

Kurze Erläuterung der FigurenBrief explanation of the figures

Die Erfindung wird nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert. Alle für das unmittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind weggelassen worden. Gleiche Elemente sind in den verschiedenen Figuren mit dem gleichen Bezugszeichen versehen. Es zeigen:

Fig. 1
eine vereinfachte perspektivische Darstellung einer mit einem Dachsegment mit Kühlbohrungen versehenen Schaufelspitze einer Gasturbinenschaufel;
Fig. 2
eine zu Fig. 1 vergleichbare Schaufel mit schräg verlaufenden Kühlbohrungen;
Fig. 3
eine gegenüber Fig. 1 vergleichbare Darstellung die mit einem Deckbandsegment mit Schlitzen versehene Schaufelspitze einer Gasturbinenschaufel gemäss einer bevorzugten Ausführung der Erfindung;
Fig. 4
den Schnitt durch das Deckbandsegment der Schaufel aus Fig. 1 in der Ebene IV-IV, wobei das Mittelstück, von dem die Kühlbohrungen ausgehen, in der Mitte liegt;
Fig. 5
den Schnitt durch das Deckbandsegment der Schaufel aus Fig. 1 in der Ebene IV-IV, wobei das Mittelstück, von dem die Kühlbohrungen ausgehen, aus der Mitte versetzt ist;
Fig. 6
den Schnitt durch das Deckbandsegment der Schaufel aus Fig. 3 in der Ebene VI-VI, wobei das Mittelstück, von dem die Kühlbohrungen ausgehen, in der Mitte liegt;
Fig. 7
im Detail eine mögliche Verbindung zwischen zwei benachbarten Deckbandsegmenten gemäss Fig. 6;
Fig. 8
eine zu Fig. 3 alternative Art, die Schlitze mit Kühlluft zu versorgen;
Fig. 9
eine in der Draufsicht gezeigte spezielle Anordnung der Kühlbohrungen benachbarter Deckbandsegmente;
Fig. 10
eine verbreiterte Nut zwischen benachbarten Deckbandsegmenten für den Austritt von Kühlluft;
Fig. 11
zusätzliche Filmkühlbohrungen, die von den Kühlbohrungen für die Schlitze abgehen;
Fig. 12
die Verteilung der Filmkühlbohrungen und
Fig. 13
die Aufteilung der Schlitze bei Anwesenheit eines Zwischenwandsegments.
The invention is explained in more detail below on the basis of exemplary embodiments in connection with the drawing. All elements not necessary for the immediate understanding of the invention have been omitted. Identical elements are provided with the same reference symbols in the various figures. Show it:
Fig. 1
a simplified perspective view of a blade tip provided with cooling bores of a gas turbine blade;
Fig. 2
one too Fig. 1 comparable blade with sloping cooling holes;
Fig. 3
one opposite Fig. 1 comparable representation of the blade tip of a gas turbine blade provided with slots with a cover band segment according to a preferred embodiment of the invention;
Fig. 4
the section through the shroud segment of the blade Fig. 1 in the plane IV-IV, with the center piece, from which the cooling holes originate, in the middle;
Fig. 5
the section through the shroud segment of the blade Fig. 1 in the plane IV-IV, with the center piece, from which the cooling holes originate, is offset from the center;
Fig. 6
the section through the shroud segment of the blade Fig. 3 in level VI-VI, with the center piece from which the cooling holes originate in the middle;
Fig. 7
in detail according to a possible connection between two adjacent shroud segments Fig. 6 ;
Fig. 8
one too Fig. 3 alternative way of supplying the slots with cooling air;
Fig. 9
a special arrangement shown in plan view of the cooling holes of adjacent shroud segments;
Fig. 10
a widened groove between adjacent shroud segments for the exit of cooling air;
Fig. 11
additional film cooling holes that extend from the cooling holes for the slots;
Fig. 12
the distribution of the film cooling holes and
Fig. 13
the division of the slots in the presence of a partition segment.

Wege zur Ausführung der ErfindungWays of Carrying Out the Invention

In Fig. 1, 2, 4 und 5 ist in perspektivischer Ansicht bzw. im Querschnitt die mit einem Deckbandsegment versehene Schaufelspitze einer Gasturbinenschaufel dargestellt. Die Schaufel 10', von der nur der obere Teil des Schaufelblatts 11 mit dem Deckbandsegment 12' gezeigt ist, hat ein gekühltes Deckbandsegment 12'.In 1, 2 , 4th and 5 is shown in perspective view or in cross section the blade tip of a gas turbine blade provided with a shroud segment. The blade 10 ', of which only the upper part of the blade 11 is shown with the shroud segment 12', has a cooled shroud segment 12 '.

Das im gezeigten Beispiel in der Grundfläche näherungsweise rechteckige Deckbandsegment 12' ist an zwei gegenüberliegenden Seiten durch vergleichsweise hohe Wandsegmente 14 und 15 begrenzt, die zusammen mit den Wandsegmenten der anderen Schaufeln einer vollständigen Schaufelreihe ringförmig umlaufende Wände bilden, zwischen denen sich ein Deckbandhohlraum ausbildet, der gegen das Eindringen von Heissgas aus dem darunter liegenden Heissgaskanal abgedichtet ist. Hierzu sind an den beiden anderen Seiten des Deckbandsegments 12' kantenparallele, nach oben abstehende Seitenschienen 16, 17 ausgebildet, mit denen benachbarte Deckbandsegmente der Schaufelreihe aneinander stossen.The approximately rectangular shroud segment 12 'in the example shown in the base area is delimited on two opposite sides by comparatively high wall segments 14 and 15 which, together with the wall segments of the other blades of a complete row of blades, form annular circumferential walls between which a shroud cavity is formed which against the penetration of hot gas from the hot gas duct underneath is sealed. For this purpose, on the two other sides of the shroud segment 12 ', parallel, upwardly projecting side rails 16, 17 are formed, with which adjacent shroud segments of the row of blades abut one another.

Zur Kühlung des vom Heissgas beaufschlagten Deckbandsegments 12 sind besondere Massnahmen vorgesehen: In der Mitte zwischen den beiden Seitenschienen 16, 17 (Fig. 4) oder seitlich aus der Mitte versetzt (Fig. 5) ist parallel dazu ein rippenartiges, innen hohles Mittelstück 13 angeordnet, das mit den im Inneren des Schaufelblattes 11 in radialer Richtung verlaufenden Kühlluftkanälen in Verbindung steht. Von dem Mittelstück 13 aus, das parallel oder quasi-parallel zu den Seitenschienen 16, 17 verläuft, erstrecken sich quer zu den Seitenschienen 16, 17 zu beiden Seiten des Mittelstücks auf der Oberseite des Deckbandsegments 12' angeformte Kühlrohre 18 auf die Seitenschienen 16, 17 zu und enden in einem Abstand vor den Seitenschienen 16, 17. Im Beispiel der Fig. 1 sind auf beiden Seiten des Mittelstücks 13 je vier parallele Kühlrohre 18 vorgesehen, die parallel oder quasi-parallel zu den Wandsegmenten 14, 15 verlaufen. Sie können aber auch schräg zu den Wandsegmenten 14, 15 orientiert sein (Fig. 2).Special measures are provided for cooling the cover band segment 12 acted upon by the hot gas: in the middle between the two side rails 16, 17 ( Fig. 4 ) or laterally offset from the center ( Fig. 5 ), a rib-like, internally hollow center piece 13 is arranged parallel to it, which is connected to the cooling air channels running in the radial direction inside the airfoil 11. From the center piece 13, which runs parallel or quasi-parallel to the side rails 16, 17, cooling tubes 18, which are molded onto the side rails 16, 17, extend transversely to the side rails 16, 17 on both sides of the center piece on the upper side of the shroud segment 12 ' to and end at a distance in front of the side rails 16, 17. In the example of Fig. 1 four parallel cooling tubes 18 are provided on both sides of the center piece 13, which run parallel or quasi-parallel to the wall segments 14, 15. However, they can also be oriented at an angle to the wall segments 14, 15 ( Fig. 2 ).

Durch den Abstand zwischen dem Rohrende 19 der Kühlrohre 18 und den Seitenschienen 16, 17 entsteht ein Zwischenraum 22. In diesen Zwischenraum 22 strömt die Kühlluft aus, die durch die Kühlbohrungen 21 im Inneren der Kühlrohre 18 fliesst und so konvektiv das Deckbandsegment 12' kühlt. Die durch die Kühlrohre 18 strömende Kühlluft stammt aus der Kühlluftzufuhr 20 im Inneren des Mittelstücks 13, mit der die Kühlbohrungen 21 in Verbindung stehen, und in die von unten ein Kühlluftstrom 25 eintritt.Due to the distance between the tube end 19 of the cooling tubes 18 and the side rails 16, 17, an intermediate space 22 is created. The cooling air flows out into this intermediate space 22, which flows through the cooling bores 21 in the interior of the cooling tubes 18 and thus convectively cools the shroud segment 12 '. The cooling air flowing through the cooling pipes 18 comes from the cooling air supply 20 in the interior of the middle piece 13, with which the cooling bores 21 are connected and into which a cooling air flow 25 enters from below.

Die aus den Kühlrohren 18 in den Zwischenraum 22 austretende Kühlluft strömt von dort in den darüber liegenden Deckbandhohlraum ein, ohne die Seitenschienen 16, 17 intensiv zu kühlen. Hier werden somit Massnahmen implementiert, durch welche die aus einem massiven Material bestehenden Seitenschienen noch besser gekühlt werden, um die thermische Belastung der Seitenschienen zu verringern und thermische Spannungen zwischen den Seitenschienen und dem übrigen Bereich der Deckbandsegmente abzubauen.The cooling air emerging from the cooling tubes 18 into the intermediate space 22 flows from there into the cover band cavity lying above, without intensively cooling the side rails 16, 17. Measures are implemented here by which the side rails made of a solid material are cooled even better in order to reduce the thermal load on the side rails and to reduce thermal stresses between the side rails and the remaining area of the cover band segments.

In den Fig. 3 und 6 sind in einer zu Fig. 1 bzw. 4 vergleichbaren Darstellung die mit einem Deckbandsegment versehene Schaufelspitze einer Gasturbinenschaufel gemäss einem bevorzugten Ausführungsbeispiel der Erfindung und der Schnitt durch das Deckbandsegment der Schaufel aus Fig. 3 in der Ebene VI-VI wiedergegeben.In the Fig. 3 and 6 are in one too Fig. 1 or 4 comparable representation of the blade tip of a gas turbine blade provided with a shroud segment according to a preferred exemplary embodiment of the invention and the section through the shroud segment of the blade Fig. 3 reproduced in the level VI-VI.

Das Deckbandsegment 12 der Schaufel 10 aus Fig. 3 und 6 ist im Unterschied zur bisherigen Lösung der Fig. 1 und 4 so ausgestaltet, dass die Seitenschienen 16, 17 nunmehr auch konvektiv gekühlt werden. Dazu sind die Kühlrohre 18 nunmehr unter Aufgabe des Zwischenraums direkt bis zu den Seitenschienen 16, 17 geführt. In die Seitenschienen 16, 17 ist jeweils ein schienenparalleler Schlitz 23, 24 eingebracht, der mit den Kühlbohrungen 21 der Kühlrohre 18 in Verbindung steht. Diese Schlitze können auch quasi-schienenparallel angeordnet sein, was auch für die Schlitze 23.1, 23.2 aus Fig. 13 gilt.The cover band segment 12 of the blade 10 Fig. 3 and 6 is different from the previous solution Fig. 1 and 4th designed so that the side rails 16, 17 are now also convectively cooled. For this purpose, the cooling pipes 18 are now led directly to the side rails 16, 17, giving up the intermediate space. In each of the side rails 16, 17 there is a slot 23, 24 which is parallel to the rail and is connected to the cooling bores 21 of the cooling tubes 18. These slots can also be arranged quasi-parallel to the rail, which also applies to the slots 23.1, 23.2 Fig. 13 applies.

Die durch die Kühlbohrungen 21 strömende Kühlluft tritt in die Schlitze 23, 24 aus und von dort in den Deckbandhohlraum ein. Auf diese Weise werden auch die Seitenschienen 16, 17 auf der Länge der Schlitze 23, 24 auf effektive Weise konvektiv gekühlt, ohne dass ein zusätzlicher, die Effektivität der Turbine beeinträchtigender Kühlluftmassenstrom, erforderlich ist. Die verteilt angeordneten Kühlrohre 18 sorgen dabei dafür, dass die Schlitze 23, 24 über ihre gesamte Länge gleichmässig mit Kühlluft versorgt werden.The cooling air flowing through the cooling bores 21 exits into the slots 23, 24 and from there into the shroud cavity. In this way, the side rails 16, 17 are also convectively cooled along the length of the slots 23, 24, without the need for an additional cooling air mass flow which impairs the effectiveness of the turbine. The distributed cooling tubes 18 ensure that the slots 23, 24 are supplied with cooling air evenly over their entire length.

Die Kühlrohre 18 sind bei der in Fig. 3 bzw. 6 gezeigten Ausführungsform auf der Oberseite des Deckbandsegments 12 (beim Giessen der Schaufel 10) angeformt und haben so eine enge thermische Ankopplung an den Körper des Deckbandsegments 12. In die Kühlrohre 18 sind von aussen die Kühlbohrungen 21 eingebracht, die nach aussen hin wieder verschlossen werden. Die Kühlrohre 18 können dabei parallel zu den Wandsegmenten 14, 15 verlaufen, wie dies in Fig. 3 dargestellt ist. Sie können aber auch gemäss Fig. 2 schräg zu den Wandsegmenten 14, 15 orientiert sein. Desgleichen kann das Mittelstück - wie in Fig. 6 gezeigt - genau in der Mitte zwischen den Wandsegmenten 14, 15 angeordnet sein. Es kann aber auch analog zu Fig. 5 aus der Mitte versetzt sein.The cooling tubes 18 are in the Fig. 3 6 or 6 shown embodiment formed on the top of the shroud segment 12 (when the blade 10 is being cast) and thus have a close thermal coupling to the body of the shroud segment 12. The cooling bores 21 are introduced into the cooling tubes 18 from the outside, and again towards the outside be closed. The cooling tubes 18 can run parallel to the wall segments 14, 15, as shown in FIG Fig. 3 is shown. But you can also according to Fig. 2 be oriented obliquely to the wall segments 14, 15. Likewise, the middle piece - as in Fig. 6 shown - be located exactly in the middle between the wall segments 14, 15. But it can also be analogous to Fig. 5 be offset from the center.

Beim Zusammenbau des Schaufelkranzes wird gemäss Fig. 7 zwischen den aneinander stossenden Deckbandsegmenten benachbarter Schaufeln 10a und 10b mit ihren Kühlbohrungen 21a und 21 b und ihren Schlitzen 24a und 23b eine streifenförmige Dichtung 26 eingefügt, die das Eindringen der Heissgase vom Heissgaskanal in den Deckbandhohlraum verhindert bzw. behindert.When assembling the blade ring according to Fig. 7 a strip-shaped seal 26 is inserted between the abutting cover band segments of adjacent blades 10a and 10b with their cooling bores 21a and 21b and their slots 24a and 23b, which prevents or impedes the penetration of the hot gases from the hot gas channel into the cover band cavity.

Anstelle der oder zusätzlich zu den Kühlrohre(n) 18 mit den Kühlbohrungen 21 können in den Wandsegmenten 14, 15 bzw. den Seitenschienen 16, 17 Kühlbohrungen 27, 28 (siehe auch Fig. 8) eingebracht sein, durch die Kühlluft zu den Schlitzen gelangt und gleichzeitig noch eine konvektive Kühlung der verdickten Deckbandbereiche bewirkt. Von diesen Kühlbohrungen können dann - wie in Fig. 11 gezeigt - Filmkühlungsbohrungen 30 abgehen, die in den unterhalb des Deckbandsegments liegenden Heissgaskanal münden und dort eine Filmkühlung der Deckbandunterseite bewirken. Dies gilt gemäss Fig. 12 auch für die Kühlbohrungen 21. Eine in den Seitenschienen 16, 17 verlaufende Kühlbohrung 28 kann gemäss Fig. 13 auch zwei getrennte Schlitze 23.1 und 23.2 untereinander verbinden, wenn das Deckbandsegment mit einem parallel zwischen den Wandsegmenten 14, 15 angeordneten Zwischenwandsegment 31 versehen ist.Instead of or in addition to the cooling tubes 18 with the cooling bores 21, cooling bores 27, 28 can be provided in the wall segments 14, 15 or the side rails 16, 17 (see also Fig. 8 ) be introduced, through the cooling air to the slots and at the same time still convective cooling of the thickened cover band areas. From these cooling holes - as in Fig. 11 shown - go off film cooling bores 30, which open into the hot gas channel lying below the shroud segment and there cause film cooling of the underside of the shroud. This applies according to Fig. 12 also for the cooling bores 21. A cooling bore 28 running in the side rails 16, 17 can according to Fig. 13 also connect two separate slots 23.1 and 23.2 to one another if the shroud segment is provided with an intermediate wall segment 31 arranged in parallel between the wall segments 14, 15.

Weiterhin kann gemäss Fig. 10 zwischen den aneinander grenzenden Deckbandsegmenten benachbarter Schaufeln 10a und 10b mit ihren Seitenschienen 17a und 16b ein erweiterter nutförmiger Zwischenraum 29 vorgesehen werden, der mit Kühlluft aus den Kühlbohrungen 21a, 21b aufgefüllt wird und so das Eindringen von Heissgasen unterbindet. Besonders vorteilhaft ist in diesem Fall für eine gleichmässige Füllung, wenn die Kühlrohre 18a, 18b dann gemäss Fig. 9 "auf Lücke" gegenüber der benachbarten Schaufel angeordnet sind.Furthermore, according to Fig. 10 Between the adjoining shroud segments of adjacent blades 10a and 10b with their side rails 17a and 16b, an enlarged groove-shaped space 29 is provided, which is filled with cooling air from the cooling bores 21a, 21b and thus prevents the penetration of hot gases. In this case, it is particularly advantageous for uniform filling if the cooling tubes 18a, 18b are then in accordance with FIG Fig. 9 "on gap" are arranged opposite the adjacent blade.

BezugzeichenlisteReference list

10,10'10.10 '
Schaufel (Gasturbine)Blade (gas turbine)
10a,b10a, b
Schaufel (Gasturbine)Blade (gas turbine)
1111
SchaufelblattAirfoil
12,12'12.12 '
DeckbandsegmentShroud segment
1313
MittelstückCenterpiece
13a,b13a, b
MittelstückCenterpiece
14,1514.15
WandsegmentWall segment
16,1716.17
SeitenschieneSide rail
17a,16b17a, 16b
SeitenschieneSide rail
18,18'18.18 '
KühlrohrCooling pipe
1919th
RohrendePipe end
2020th
KühlluftzufuhrCooling air supply
21,27,2821,27,28
KühlbohrungCooling hole
2222
ZwischenraumSpace
23,2423.24
Schlitzslot
23b,24a23b, 24a
Schlitzslot
23.1,23.223.1,23.2
Schlitzslot
2525th
KühlluftstromCooling air flow
2626
Dichtungpoetry
2929
ZwischenraumSpace
3030th
FilmkühlbohrungFilm cooling hole
3131
ZwischenwandsegmentPartition wall segment

Claims (14)

  1. Blade (10) for a gas turbine, comprising a vane blade (11) with a cover strip segment (12) arranged on its upper end, which cover strip segment (12) together with the cover strip segments of the adjacent blades of a blade row forms an annular cover strip delimiting the hot gas channel of the gas turbine, and which cover strip segment (12), at the sides at which it adjoins the adjacent cover strip segments of the cover strip, is provided with upwardly protruding side rails (16, 17) which run along the side edge to improve the seal against the hot gas channel, characterised in that to maximise cooling in the region of the side rails (16, 17), slots (23, 24; 23.1, 23.2) which are open at the top are arranged in the side rails (16, 17) parallel or quasi-parallel to the rails, through which cooling air extracted from the interior of the vane blade (11) can emerge via the cover strip segment (12) into the space above the cover strip segment (12).
  2. Blade according to claim 1, characterised in that on the top of the cover strip segment (12), a plurality of cooling tubes (18) are arranged which run transversely to the side rails (16, 17), wherein said tubes start from a centre piece (13) arranged between the side rails (16, 17) from where they can be loaded with cooling air, terminate in the side rails (16, 17), and are connected to the slots (23, 24) in the side rails (16, 17).
  3. Blade according to claim 2, characterised in that the centre piece (13) is arranged, in the sense of a geometric location, in the middle between the side rails (16, 17).
  4. Blade according to claim 2, characterised in that the centre piece (13) is arranged, in the sense of a geometric location, offset to the middle between the side rails (16, 17).
  5. Blade according to claim 3 or 4, characterised in that the cooling tubes (18) run parallel or quasi-parallel to each other, and that the centre piece (13) extends substantially parallel or quasi-parallel to the side rails (16, 17).
  6. Blade according to claim 5, characterised in that the cooling tubes (18) run in the circumferential direction of the cover strip.
  7. Blade according to claim 5, characterised in that the cooling tubes (18) run obliquely to the circumferential direction of the cover strip.
  8. Blade according to any of claims 2 to 7, characterised in that the cooling tubes (18) each have a cooling bore (21) and are configured for convective cooling of the cover strip segment (12).
  9. Blade according to any of claims 2 to 8, characterised in that the cooling tubes (18) are moulded onto the cover strip segment (12).
  10. Blade according to any of claims 2 to 9, characterised in that the cooling tubes (18a, 18b) of blades (10a, 10b) which adjoin each other with their cover strip segments are arranged with gaps.
  11. Blade according to claim 1, characterised in that the cover strip segment (12) is delimited in the axial direction by wall segments (14, 15) extending in the circumferential direction, and that the cooling air emerging from the slots (23, 24; 23.1, 23.2) is supplied via cooling bores (27, 28) in the region of the wall segments (14, 15) and side rails (16, 17).
  12. Blade according to any of claims 1 to 11, characterised in that the cover strip segment (12) is delimited in the axial or quasi-axial direction by wall segments (14, 15) extending in the circumferential direction, and that an intermediate wall segment (31) is provided which runs parallel or quasi-parallel to the wall segments (14, 15) and is arranged, in the sense of a geometric location, in the middle between the wall segments (14, 15), and that a slot (23.1, 23.2) is provided in each side rail (16, 17) between the intermediate wall segment (31) and the wall segments (14, 15).
  13. Blade according to claim 12, characterised in that the slots (23.1, 23.2) of a side rail are connected together by a respective cooling bore (28) running in the side rail.
  14. Blade according to any of claims 1 to 13, characterised in that film cooling bores (30) depart from the cooling bores (21, 27, 28) supplying the slots (23, 24) and open into the hot gas channel on the underside of the cover strip segment (12).
EP10706671.4A 2009-03-30 2010-03-05 Blade for a gas turbine Active EP2414640B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00502/09A CH700686A1 (en) 2009-03-30 2009-03-30 Blade for a gas turbine.
PCT/EP2010/052867 WO2010112299A1 (en) 2009-03-30 2010-03-05 Blade for a gas turbine

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EP2414640A1 EP2414640A1 (en) 2012-02-08
EP2414640B1 true EP2414640B1 (en) 2020-05-27

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US (1) US9464529B2 (en)
EP (1) EP2414640B1 (en)
AU (1) AU2010230482B2 (en)
CH (1) CH700686A1 (en)
RU (1) RU2543641C2 (en)
WO (1) WO2010112299A1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8807927B2 (en) * 2011-09-29 2014-08-19 General Electric Company Clearance flow control assembly having rail member
US20130315719A1 (en) * 2012-05-25 2013-11-28 General Electric Company Turbine Shroud Cooling Assembly for a Gas Turbine System
US9683446B2 (en) * 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
US9759070B2 (en) * 2013-08-28 2017-09-12 General Electric Company Turbine bucket tip shroud
US9556741B2 (en) 2014-02-13 2017-01-31 Pratt & Whitney Canada Corp Shrouded blade for a gas turbine engine
EP3269932A1 (en) * 2016-07-13 2018-01-17 MTU Aero Engines GmbH Shrouded gas turbine blade
US10947898B2 (en) 2017-02-14 2021-03-16 General Electric Company Undulating tip shroud for use on a turbine blade
US10704406B2 (en) 2017-06-13 2020-07-07 General Electric Company Turbomachine blade cooling structure and related methods
US11060407B2 (en) 2017-06-22 2021-07-13 General Electric Company Turbomachine rotor blade
US10577945B2 (en) 2017-06-30 2020-03-03 General Electric Company Turbomachine rotor blade
US10301943B2 (en) 2017-06-30 2019-05-28 General Electric Company Turbomachine rotor blade
US10590777B2 (en) 2017-06-30 2020-03-17 General Electric Company Turbomachine rotor blade
US10753207B2 (en) 2017-07-13 2020-08-25 General Electric Company Airfoil with tip rail cooling
US10641108B2 (en) * 2018-04-06 2020-05-05 United Technologies Corporation Turbine blade shroud for gas turbine engine with power turbine and method of manufacturing same
US11255198B1 (en) * 2021-06-10 2022-02-22 General Electric Company Tip shroud with exit surface for cooling passages

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605335A (en) * 1975-08-23 1991-12-18 Rolls Royce A rotor blade for a gas turbine engine
GB9224241D0 (en) * 1992-11-19 1993-01-06 Bmw Rolls Royce Gmbh A turbine blade arrangement
US5482435A (en) * 1994-10-26 1996-01-09 Westinghouse Electric Corporation Gas turbine blade having a cooled shroud
GB2298246B (en) * 1995-02-23 1998-10-28 Bmw Rolls Royce Gmbh A turbine-blade arrangement comprising a shroud band
US5779447A (en) * 1997-02-19 1998-07-14 Mitsubishi Heavy Industries, Ltd. Turbine rotor
US5785496A (en) * 1997-02-24 1998-07-28 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
JP3510467B2 (en) * 1998-01-13 2004-03-29 三菱重工業株式会社 Gas turbine blades
EP2157280B1 (en) * 1998-02-04 2015-12-02 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine rotor blade
DE59912323D1 (en) * 1998-12-24 2005-09-01 Alstom Technology Ltd Baden Turbine blade with actively cooled Deckbandelememt
US6761534B1 (en) * 1999-04-05 2004-07-13 General Electric Company Cooling circuit for a gas turbine bucket and tip shroud
DE19963377A1 (en) * 1999-12-28 2001-07-12 Abb Alstom Power Ch Ag Turbine blade with actively cooled cover band element
EP1591625A1 (en) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Gas turbine blade shroud
US7284954B2 (en) * 2005-02-17 2007-10-23 Parker David G Shroud block with enhanced cooling
JP4628865B2 (en) * 2005-05-16 2011-02-09 株式会社日立製作所 Gas turbine blade, gas turbine using the same, and power plant
RU60631U1 (en) * 2006-08-21 2007-01-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" GAS-TURBINE ENGINE SHOULDER BAND SHELF
US7762774B2 (en) * 2006-12-15 2010-07-27 Siemens Energy, Inc. Cooling arrangement for a tapered turbine blade
US7568882B2 (en) * 2007-01-12 2009-08-04 General Electric Company Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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EP2414640A1 (en) 2012-02-08
AU2010230482A1 (en) 2011-10-13
US9464529B2 (en) 2016-10-11
CH700686A1 (en) 2010-09-30
US20120070309A1 (en) 2012-03-22
AU2010230482B2 (en) 2014-12-04
WO2010112299A1 (en) 2010-10-07
RU2011143766A (en) 2013-05-10
RU2543641C2 (en) 2015-03-10

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