EP2313615B1 - Blade arrangement of a gas turbine - Google Patents

Blade arrangement of a gas turbine Download PDF

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Publication number
EP2313615B1
EP2313615B1 EP09781705.0A EP09781705A EP2313615B1 EP 2313615 B1 EP2313615 B1 EP 2313615B1 EP 09781705 A EP09781705 A EP 09781705A EP 2313615 B1 EP2313615 B1 EP 2313615B1
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EP
European Patent Office
Prior art keywords
blade
heat shield
coating
blade tip
gas turbine
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EP09781705.0A
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German (de)
French (fr)
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EP2313615A1 (en
EP2313615B2 (en
Inventor
Thomas Heinz-Schwarzmaier
Thomas Duda
Alexander Schnell
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Ansaldo Energia IP UK Ltd
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Alstom Technology AG
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    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Definitions

  • the present invention relates to the field of thermal turbomachines, in particular gas turbines. It relates to a blade arrangement of a thermal turbomachine according to the preamble of claim 1.
  • blade arrangements 20 are according to FIG Fig. 2 have been proposed (see for example the EP-A2-0 166 676 .
  • EP-A2-1 312 760 or the US A1-2008166225 ) in which at the blade tip 27 of the blades in a support layer 19 embedded abrasive (grains) 21 (eg silicon carbide or cubic boron nitride cBN) are arranged, with which the blade tip 27 in operation in an abradable thermal barrier coating 18 (Thermal Barrier Coating TBC ) can grind on the opposite heat shield 12.
  • a layer of metallic MCrAlY may be used as the carrier layer 19 for the abrasive bodies 21, as well as the adhesive layer 17 under the thermal barrier coating 18.
  • the abrasive layer 19, 21 of such a blade arrangement is constructed comparatively complex by the embedded abrasive body and therefore expensive to manufacture.
  • EP-A2-0 965 730 discloses suitable combinations of materials of interacting abrasive and abradable surfaces in gas turbines, particularly heat shield and blade tip, based on an abrasive blade tip and an abradably equipped surface of the heat shield.
  • the Heat shield has an erosion-resistant surface made of a first ceramic material, which is firmly connected by means of an adhesive layer to the substrate. In a limited area, the contact area with the rotating blade tip, an abradable wear layer of a second ceramic material is applied.
  • the acting blade tip is with an abrasive coating, preferably according to US-A-4,936,745 , So with embedded in a metallic support layer grinding bodies of silicon carbide or cubic boron nitride equipped. This solution is also characterized by elaborately equipped surfaces of the components involved.
  • Blade tip and heat shield have means that allow a targeted grinding of the blade tip in the heat shield.
  • the heat shield itself has as its outer layer a porous thermal barrier coating with polygonal depressions (FIG. 6) or circumferentially extending grooves defined by wall projections (FIGS. 7, 8), while the blade tip is provided with a peripheral cutting edge (FIGS. 4, 5) ) is equipped for cutting into the abradable coating of the heat shield.
  • the equipment of the blade tip with circumferential cutting edges increases the production effort and - at least when used in the gas turbine - the cost of blade cooling in this area.
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a blade arrangement which avoids the disadvantages of known blade arrangements and, with a simple structure, produces a comparable loop-in behavior without the need to provide a special abrasive layer on the blade tip.
  • the heat shield as an external, abradable Layer has a porous thermal barrier coating of a porous ceramic layer, and that the blade tip is provided only with a homogeneous metallic cover layer of MCrAIY.
  • the porous thermal barrier coating allows the blade tip covered with the cover layer to be looped into the heat shield without special abrasive particles or abrasive layer, thereby optimally minimizing play between the blade tip and the opposite heat shield.
  • the blade is a blade or a vane of a thermal turbomachine, in particular a gas turbine, wherein in the case of a vane of the blade tip is opposite to a heat shield attached to the rotor.
  • the blade is a rotating blade about the axis, while the heat shield is fixedly mounted on the stator of the gas turbine.
  • porous ceramic layer consists of YSZ.
  • porosity of the thermal barrier coating is greater than 20%.
  • an adhesive layer in particular of MCrAIY, is advantageously arranged.
  • Another embodiment is characterized in that the blade is part of the first blade row in the turbine part of the gas turbine.
  • Fig. 3 is a preferred embodiment of a blade assembly 30 according to the invention reproduced.
  • a rotatable about the axis 16 of the gas turbine blade 11 with the blade tip 27 a heat shield 12 with game 25 opposite.
  • the clearance 25 and thus the efficiency of the turbine are optimized by grinding the blade tip 27 into the coating 22, 23 of the heat shield 12 (in Fig. 3 the possible grinding area 28 on the heat shield is indicated by a dashed line).
  • a heat-insulating layer 23 is provided on the heat shield 12, which is connected to the substrate of the heat shield 12 via an adhesive layer 22 lying therebetween.
  • the adhesive layer 22 may be provided in a conventional manner, a metallic oxidation protection layer of MCrAIY.
  • the abrasion at the blade tip 27 in comparison to the depth of the grinding-in region 28 during grinding is comparatively small, so that a special grinding layer on the blade tip 27 can be dispensed with. It is therefore sufficient if the blade tip 27 is covered with a homogeneous cover layer 24 (without abrasive particles) of MCrAlY, which is provided as a protective layer against the oxidation of the blade material in any case.

Description

Technisches GebietTechnical area

Die vorliegende Erfindung bezieht sich auf das Gebiet der thermischen Strömungsmaschinen, insbesondere der Gasturbinen. Sie betrifft eine Schaufelanordnung einer thermischen Strömungsmaschine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of thermal turbomachines, in particular gas turbines. It relates to a blade arrangement of a thermal turbomachine according to the preamble of claim 1.

Stand der TechnikState of the art

Für den Wirkungsgrad einer Gasturbine ist es von grosser Wichtigkeit, insbesondere im Turbinenteil, in dem die heissen Gase aus der Brennkammer entspannt werden, die zwischen dem beschaufelten drehenden Rotor und dem umgebenden Stator auftretenden Spalte im Bereich der Beschaufelung möglichst klein zu halten.For the efficiency of a gas turbine, it is of great importance, especially in the turbine part in which the hot gases are released from the combustion chamber, to keep the gap between the bladed rotating rotor and the surrounding stator as small as possible in the area of the blading.

Im einfachsten Fall, wie dies in Fig. 1 anhand der Schaufelanordnung 10 wiedergegeben ist, werden für eine Optimierung der Spaltbreite keine speziellen Massnahmen ergriffen: Die in den Heissgaskanal 13 der Gasturbine radial hineinragenden, um die Achse 16 drehenden Laufschaufeln 11 enden in einer mit einer ersten Abdeckschicht 15 versehenen Schaufelspitze 27, die mit einem Spiel 25 einem die äussere Wand 26 des Heissgaskanals 13 bildenden Hitzeschild 12 gegenüberliegt, welcher mit einer zweiten Abdeckschicht 14 versehen ist. Die Abdeckschichten 14 und 15, die beispielsweise aus MCrAIY bestehen können, schützen die Bauteile 11 und 12 vor den schädlichen Einwirkungen der heissen Gase im Heissgaskanal 13, insbesondere vor unerwünschter Oxidation. Die Schaufelanordnung 10 der Fig. 1 ist nicht für ein Einschleifen der Schaufelspitzen 27 in den Hitzeschild 12 ausgelegt. Das Spiel 25 zwischen den Schaufelspitzen 27 und dem Hitzeschild 12 berücksichtigt die verschiedenen Wärmedehnungen und ist daher vergleichsweise gross, um ein Schleifen der Bauteile im Betrieb zu vermeiden.In the simplest case, like this in Fig. 1 With reference to the blade assembly 10, no special measures are taken to optimize the gap width: The radially projecting into the hot gas duct 13 of the gas turbine, rotating about the axis 16 blades 11 terminate in a provided with a first cover 15 blade tip 27, which with a Game 25 a the outer wall 26 of the hot gas channel 13 forming heat shield 12 is opposite, which is provided with a second cover layer 14. The cover layers 14 and 15, which may consist of MCrAlY for example, protect the components 11 and 12 against the harmful effects of the hot gases in the hot gas duct 13, in particular against undesired oxidation. The blade assembly 10 of Fig. 1 is not designed for grinding the blade tips 27 into the heat shield 12. The game 25 between the blade tips 27th and the heat shield 12 takes into account the different thermal expansions and is therefore comparatively large, in order to avoid grinding of the components during operation.

Um das Spiel 25 reduzieren zu können, sind Schaufelanordnungen 20 gemäss Fig. 2 vorgeschlagen worden (siehe z.B. die EP-A2-0 166 676 , EP-A2-1 312 760 oder die US-A1-2008166225 ), bei denen an der Schaufelspitze 27 der Laufschaufeln in eine Trägerschicht 19 eingebettet Schleifkörper (Körner) 21 (z.B. aus Siliziumkarbid oder kubischem Bornitrid cBN) angeordnet sind, mit denen sich die Schaufelspitze 27 im Betrieb in eine abschleifbare Wärmedämmschicht 18 (Thermal Barrier Coating TBC) auf dem gegenüberliegenden Hitzeschild 12 einschleifen kann. Als Trägerschicht 19 für die Schleifkörper 21 kann beispielsweise eine Schicht aus metallischem MCrAIY verwendet werden, ebenso wie als Haftschicht 17 unter der Wärmedämmschicht 18.In order to be able to reduce the clearance 25, blade arrangements 20 are according to FIG Fig. 2 have been proposed (see for example the EP-A2-0 166 676 . EP-A2-1 312 760 or the US A1-2008166225 ), in which at the blade tip 27 of the blades in a support layer 19 embedded abrasive (grains) 21 (eg silicon carbide or cubic boron nitride cBN) are arranged, with which the blade tip 27 in operation in an abradable thermal barrier coating 18 (Thermal Barrier Coating TBC ) can grind on the opposite heat shield 12. For example, a layer of metallic MCrAlY may be used as the carrier layer 19 for the abrasive bodies 21, as well as the adhesive layer 17 under the thermal barrier coating 18.

Die Schleifschicht 19, 21 einer solchen Schaufelanordnung ist durch die eingelagerten Schleifkörper vergleichsweise komplex aufgebaut und daher aufwändig in der Herstellung.The abrasive layer 19, 21 of such a blade arrangement is constructed comparatively complex by the embedded abrasive body and therefore expensive to manufacture.

Dokument US-A1-5 883 314 offenbart ein Verfahren zur Herstellung abreibbarer Beschichtungen auf thermisch beanspruchten Komponenten von Gasturbinen, welche sich durch gute Abriebeigenschaften bei gleichzeitig hoher Bindungswirkung an das Substrat auszeichnen. Einsatzgebiete sind Statorteile des Heißgaskanals oder Schaufelteile. Schichtartig aufgebaute biegsame Vorformlinge auf Basis modifizierter MCrAIY-Legierungen werden auf die fraglichen Bereiche der Turbinenkomponente, beispielsweise die Schaufelspitze, aufgebracht und mit ihr metallurgisch verbunden. Die Herstellung der mehrschichtigen Vorformlinge ist vergleichsweise aufwändig.document US-A1-5,883,314 discloses a method for producing abradable coatings on thermally stressed components of gas turbines, which are characterized by good Abriebeigenschaften with high binding effect to the substrate. Fields of application are stator parts of the hot gas channel or blade parts. Layered flexible preforms based on modified MCrAlY alloys are applied to and metallurgically bonded to the areas of the turbine component in question, for example the blade tip. The production of the multilayer preforms is comparatively complicated.

EP-A2-0 965 730 offenbart geeignete Materialkombinationen in Wechselwirkung stehender abrasiver und abreibbarer Oberflächen in Gasturbinen, insbesondere Hitzeschild und Laufschaufelspitze, basierend auf einer abrasiv ausgerüsteten Schaufelspitze und einer abreibbar ausgerüsteten Oberfläche des Hitzeschilds. Der Hitzeschild besitzt eine erosionsbeständige Oberfläche aus einem ersten keramischen Material, welche mittels einer Haftschicht fest mit dem Substrat verbunden ist. In einem begrenzten Bereich, dem Kontaktbereich mit der rotierenden Schaufelspitze, ist eine abreibbare Verschleißschicht aus einem zweiten keramischen Material aufgebracht. Die einwirkende Laufschaufelspitze ist mit einer abrasiven Beschichtung, vorzugsweise gemäß US-A-4 936 745 , also mit in eine metallische Trägerschicht eingebetteten Schleifkörpern aus Siliziumkarbid oder kubischem Bornitrid, ausgerüstet. Auch diese Lösung zeichnet sich durch aufwändig ausgerüstete Oberflächen der beteiligten Komponenten aus. EP-A2-0 965 730 discloses suitable combinations of materials of interacting abrasive and abradable surfaces in gas turbines, particularly heat shield and blade tip, based on an abrasive blade tip and an abradably equipped surface of the heat shield. Of the Heat shield has an erosion-resistant surface made of a first ceramic material, which is firmly connected by means of an adhesive layer to the substrate. In a limited area, the contact area with the rotating blade tip, an abradable wear layer of a second ceramic material is applied. The acting blade tip is with an abrasive coating, preferably according to US-A-4,936,745 , So with embedded in a metallic support layer grinding bodies of silicon carbide or cubic boron nitride equipped. This solution is also characterized by elaborately equipped surfaces of the components involved.

Die Druckschrift US-A1- 2003/175116 beschreibt eine abreibbare Beschichtung für Statorkomponenten eines Verdichters oder einer Gasturbine. Schaufelspitze und Hitzeschild weisen Mittel auf, welche ein gezieltes Einschleifen der Schaufelspitze in den Hitzeschild ermöglichen. Der Hitzeschild selbst weist als äussere Schicht eine poröse Wärmedämmschicht mit polygonalen Vertiefungen (Fig. 6) oder in Umfangsrichtung verlaufenden Nuten, begrenzt von Wandvorsprüngen (Fig. 7, 8), auf, während die Laufschaufelspitze mit einer umlaufenden Schneidkante (Fig. 4, 5) zum Einschneiden in die abreibbare Beschichtung des Hitzeschildes ausgerüstet ist. Die Ausrüstung der Schaufelspitze mit umlaufenden Schneidkanten erhöht den Herstellungsaufwand und - jedenfalls bei einem Einsatz in der Gasturbine - den Aufwand für die Schaufelkühlung in diesem Bereich.The publication US-A1- 2003/175116 describes an abradable coating for stator components of a compressor or a gas turbine. Blade tip and heat shield have means that allow a targeted grinding of the blade tip in the heat shield. The heat shield itself has as its outer layer a porous thermal barrier coating with polygonal depressions (FIG. 6) or circumferentially extending grooves defined by wall projections (FIGS. 7, 8), while the blade tip is provided with a peripheral cutting edge (FIGS. 4, 5) ) is equipped for cutting into the abradable coating of the heat shield. The equipment of the blade tip with circumferential cutting edges increases the production effort and - at least when used in the gas turbine - the cost of blade cooling in this area.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Es ist daher Aufgabe der Erfindung, eine Schaufelanordnung anzugeben, welche die Nachteile bekannter Schaufelanordnungen vermeidet und bei einfachem Aufbau ein vergleichbares Einschleifverhalten erzeugt, ohne dass an der Schaufelspitze eine spezielle Schleifschicht vorgesehen werden muss.The invention aims to remedy this situation. It is therefore an object of the invention to provide a blade arrangement which avoids the disadvantages of known blade arrangements and, with a simple structure, produces a comparable loop-in behavior without the need to provide a special abrasive layer on the blade tip.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Wesentlich für die Erfindung ist, dass der Hitzeschild als äussere, abschleifbare Schicht eine poröse Wärmedämmschicht aus einer porösen Keramikschicht aufweist, und dass die Schaufelspitze lediglich mit einer homogenen metallischen Abdeckschicht aus MCrAIY versehen ist. Die poröse Wärmedämmschicht ermöglicht es der mit der Abdeckschicht bedeckten Schaufelspitze, sich auch ohne spezielle Schleifkörper bzw. Schleifschicht in den Hitzeschild einzuschleifen und so das Spiel zwischen Schaufelspitze und gegenüberliegendem Hitzeschild optimal zu minimieren.The object is solved by the entirety of the features of claim 1. Essential for the invention is that the heat shield as an external, abradable Layer has a porous thermal barrier coating of a porous ceramic layer, and that the blade tip is provided only with a homogeneous metallic cover layer of MCrAIY. The porous thermal barrier coating allows the blade tip covered with the cover layer to be looped into the heat shield without special abrasive particles or abrasive layer, thereby optimally minimizing play between the blade tip and the opposite heat shield.

Grundsätzlich ist die Schaufel eine Laufschaufel oder eine Leitschaufel einer thermischen Strömungsmaschine, insbesondere einer Gasturbine, wobei im Falle einer Leitschaufel der Schaufelspitze ein am Rotor befestigter Hitzeschild gegenüberliegt. Gemäss einer bevorzugten Ausgestaltung ist die Schaufel eine um die Achse rotierende Laufschaufel, während der Hitzeschild am Stator der Gasturbine ortsfest montiert ist.Basically, the blade is a blade or a vane of a thermal turbomachine, in particular a gas turbine, wherein in the case of a vane of the blade tip is opposite to a heat shield attached to the rotor. According to a preferred embodiment, the blade is a rotating blade about the axis, while the heat shield is fixedly mounted on the stator of the gas turbine.

Eine andere Ausgestaltung der Erfindung zeichnet sich dadurch aus, dass die poröse Keramikschicht aus YSZ, besteht. Vorzugsweise ist dabei die Porosität der Wärmedämmschicht grösser als 20 %.Another embodiment of the invention is characterized in that the porous ceramic layer consists of YSZ. Preferably, the porosity of the thermal barrier coating is greater than 20%.

Zwischen dem Hitzeschild und der Wärmedämmschicht ist mit Vorteil eine Haftschicht, insbesondere aus MCrAIY, angeordnet.Between the heat shield and the thermal barrier coating, an adhesive layer, in particular of MCrAIY, is advantageously arranged.

Eine andere Ausgestaltung ist dadurch gekennzeichnet, dass die Laufschaufel Teil der ersten Laufschaufelreihe im Turbinenteil der Gasturbine ist.Another embodiment is characterized in that the blade is part of the first blade row in the turbine part of the 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. Es zeigen

Fig. 1
in einer stark vereinfachten Darstellung eine frühere Schaufelanordnung ohne die Möglichkeit des Einschleifens;
Fig. 2
in einer zu Fig. 1 vergleichbaren Darstellung eine andere frühere Schaufelanordnung mit einer speziellen Schleifschicht auf der Schaufelspitze und
Fig. 3
in einer zu Fig. 1 vergleichbaren Darstellung eine für das Einschleifen vorgesehen Schaufelanordnung mit einer einfachen Abdeckschicht auf der Schaufelspitze gemäss einem Ausführungsbeispiel der Erfindung.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1
in a highly simplified representation, an earlier blade arrangement without the possibility of grinding;
Fig. 2
in one too Fig. 1 Comparative illustration of another earlier blade assembly with a special abrasive layer on the blade tip and
Fig. 3
in one too Fig. 1 comparable representation of an intended for grinding blade assembly with a simple cover layer on the blade tip according to an embodiment of the invention.

Wege zur Ausführung der ErfindungWays to carry out the invention

In Fig. 3 ist ein bevorzugtes Ausführungsbeispiel für eine Schaufelanordnung 30 nach der Erfindung wiedergegeben. In dem Beispiel steht wiederum einer um die Achse 16 der Gasturbine drehbaren Laufschaufel 11 mit der Schaufelspitze 27 ein Hitzeschild 12 mit Spiel 25 gegenüber. Das Spiel 25 und damit der Wirkungsgrad der Turbine werden durch Einschleifen der Schaufelspitze 27 in die Beschichtung 22, 23 des Hitzeschilds 12 optimiert (in Fig. 3 ist der mögliche Einschleifbereich 28 am Hitzeschild durch eine gestrichelte Linie angedeutet).In Fig. 3 is a preferred embodiment of a blade assembly 30 according to the invention reproduced. In the example, in turn, a rotatable about the axis 16 of the gas turbine blade 11 with the blade tip 27 a heat shield 12 with game 25 opposite. The clearance 25 and thus the efficiency of the turbine are optimized by grinding the blade tip 27 into the coating 22, 23 of the heat shield 12 (in Fig. 3 the possible grinding area 28 on the heat shield is indicated by a dashed line).

Als beim Einschleifen abzuschleifende Schicht ist am Hitzeschild 12 eine Wärmedämmschicht 23 vorgesehen, die über eine dazwischen liegende Haftschicht 22 mit dem Substrat des Hitzeschilds 12 verbunden ist. Als Haftschicht 22 kann in üblicher Weise eine metallische Oxidationsschutzschicht aus MCrAIY vorgesehen werden.As a layer to be abraded during grinding, a heat-insulating layer 23 is provided on the heat shield 12, which is connected to the substrate of the heat shield 12 via an adhesive layer 22 lying therebetween. As the adhesive layer 22 may be provided in a conventional manner, a metallic oxidation protection layer of MCrAIY.

Bei Versuchen hat sich nun herausgestellt, dass ein Einschleifen der Schaufelspitze in die Wärmedämmschicht 23 auch ohne spezielle Schleifschicht auf der Schaufelspitze 27 möglich ist und zu guten Resultaten führt, wenn die Wärmedämmschicht 23 - ohne ihre thermischen Eigenschaften zu verlieren - ausreichend leicht abzuschleifen ist. Dies lässt sich dadurch erreichen, dass eine poröse Wärmedämmschicht 23 aus einer porösen Keramikschicht, die insbesondere aus YSZ (Yttriumoxid-stabilisiertem Zirkoniumoxid) bestehen kann, verwendet wird, wobei die Porosität beispielsweise durch eingelagerte Polymere erzeugt wird, die später ausgeheizt werden. Es hat sich dabei als vorteilhaft herausgestellt, wenn die Porosität der Wärmedämmschicht grösser als 20 % ist, also beispielsweise im Bereich von 22-24 % liegt.In experiments it has now been found that a grinding of the blade tip into the heat-insulating layer 23 is possible even without a special abrasive layer on the blade tip 27 and leads to good results when the thermal barrier coating 23 - without losing their thermal properties - is sufficiently easy to grind. This can be achieved in that a porous thermal barrier coating 23 of a porous ceramic layer, the In particular, from YSZ (yttria-stabilized zirconia) may be used, wherein the porosity is generated for example by embedded polymers, which are later heated. It has proven to be advantageous if the porosity of the thermal barrier coating is greater than 20%, that is, for example, in the range of 22-24%.

Bei einer solchen porösen Wärmedämmschicht 23 ist beim Einschleifen der Abrieb an der Schaufelspitze 27 gegenüber der Tiefe des Einschleifbereichs 28 vergleichsweise klein, so dass auf eine spezielle Schleifschicht an der Schaufelspitze 27 verzichtet werden kann. Es reicht daher aus, wenn die Schaufelspitze 27 mit einer homogenen Abdeckschicht 24 (ohne Schleifkörper) aus MCrAIY bedeckt ist, die als Schutzschicht gegen die Oxidation des Schaufelmaterials ohnehin vorgesehen ist.In the case of such a porous heat-insulating layer 23, the abrasion at the blade tip 27 in comparison to the depth of the grinding-in region 28 during grinding is comparatively small, so that a special grinding layer on the blade tip 27 can be dispensed with. It is therefore sufficient if the blade tip 27 is covered with a homogeneous cover layer 24 (without abrasive particles) of MCrAlY, which is provided as a protective layer against the oxidation of the blade material in any case.

Auf diese Weise brauchen an der Schaufel 11 keine besonderen Vorkehrungen für das Einschleifen getroffen werden, wodurch sich die Herstellung der Schaufel 11 wesentlich vereinfacht.In this way, no special measures for the grinding 11 need to be made on the blade 11, whereby the manufacture of the blade 11 is substantially simplified.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

10,20.3010,20.30
Schaufelanordnung (Gasturbine)Blade assembly (gas turbine)
1111
Laufschaufelblade
1212
Hitzeschildheat shield
1313
HeissgaskanalHot-gas duct
14,15,2414,15,24
Abdeckschichtcovering
1616
Achseaxis
17,2217.22
Haftschichtadhesive layer
18,2318.23
Wärmedämmschicht (TBC)Thermal barrier coating (TBC)
1919
Trägerschichtbacking
2121
Schleifkörperabrasives
2525
Spielgame
2626
Wand (Heissgaskanal)Wall (hot gas channel)
2727
Schaufelspitzeblade tip
2828
EinschleifbereichEinschleifbereich

Claims (6)

  1. Blade arrangement (30) of a thermal turbomachine with at least one blade (11), which in the radial direction projects into a passage (13) which is arranged concentrically to an axis (16) and is exposed to throughflow by hot gas, and terminates in a blade tip (27) which with a clearance (25) lies opposite a heat shield (12) which delimits the passage (13), wherein the blade (11) and the heat shield (12) are movable in relation to each other in the circumferential direction, and the blade tip (27) and the heat shield (12) have means (22, 23, 24) which enable a directed cutting of the blade tip (27) into the heat shield (12), and wherein the heat shield (12) has a porous thermal barrier coating (23) as an outer, abradable coating, characterized in that the porous thermal barrier coating (23) is a porous ceramic coating and in that the blade tip (27) is provided only with a homogenous, metallic cover coating (24) consisting of MCrALY.
  2. Blade arrangement according to Claim 1, characterized in that the thermal turbomachine is a gas turbine, in that the blade is a rotor blade (11) which rotates around the axis (16), and in that the heat shield (12) is installed on the stator of the gas turbine in a fixed manner.
  3. Blade arrangement according to Claim 1 and/or 2, characterized in that the porous ceramic coating consists of YSZ (yttrium oxide-stabilized zirconium oxide).
  4. Blade arrangement according to Claim 3, characterized in that the porosity of the thermal barrier coating (23) is more than 20%.
  5. Blade arrangement according to Claim 3 or 4, characterized in that an adhesion coating (22), especially consisting of MCrAlY, is arranged between the heat shield (12) and the thermal barrier coating (23).
  6. Blade arrangement according to Claim 2, characterized in that the rotor blade (11) is part of the first rotor-blade row in the turbine section of the gas turbine.
EP09781705.0A 2008-08-15 2009-08-11 Blade arrangement of a gas turbine Active EP2313615B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH01285/08A CH699312A1 (en) 2008-08-15 2008-08-15 Blade arrangement for a gas turbine.
PCT/EP2009/060387 WO2010018174A1 (en) 2008-08-15 2009-08-11 Blade arrangement of a gas turbine

Publications (3)

Publication Number Publication Date
EP2313615A1 EP2313615A1 (en) 2011-04-27
EP2313615B1 true EP2313615B1 (en) 2016-03-23
EP2313615B2 EP2313615B2 (en) 2023-09-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP09781705.0A Active EP2313615B2 (en) 2008-08-15 2009-08-11 Blade arrangement of a gas turbine

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US (1) US20110171039A1 (en)
EP (1) EP2313615B2 (en)
CH (1) CH699312A1 (en)
WO (1) WO2010018174A1 (en)

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DE102013212741A1 (en) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine
US20160237832A1 (en) * 2015-02-12 2016-08-18 United Technologies Corporation Abrasive blade tip with improved wear at high interaction rate
US20160245110A1 (en) * 2015-02-25 2016-08-25 United Technologies Corporation Hard phaseless metallic coating for compressor blade tip
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Publication number Priority date Publication date Assignee Title
DE102017207238A1 (en) * 2017-04-28 2018-10-31 Siemens Aktiengesellschaft Sealing system for blade and housing
US11274560B2 (en) 2017-04-28 2022-03-15 Siemens Energy Global GmbH & Co. KG Sealing system for a rotor blade and housing

Also Published As

Publication number Publication date
CH699312A1 (en) 2010-02-15
WO2010018174A1 (en) 2010-02-18
EP2313615A1 (en) 2011-04-27
EP2313615B2 (en) 2023-09-27
US20110171039A1 (en) 2011-07-14

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