WO2010018174A1 - Blade arrangement of a gas turbine - Google Patents

Blade arrangement of a gas turbine Download PDF

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Publication number
WO2010018174A1
WO2010018174A1 PCT/EP2009/060387 EP2009060387W WO2010018174A1 WO 2010018174 A1 WO2010018174 A1 WO 2010018174A1 EP 2009060387 W EP2009060387 W EP 2009060387W WO 2010018174 A1 WO2010018174 A1 WO 2010018174A1
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WO
WIPO (PCT)
Prior art keywords
blade
heat shield
layer
blade tip
barrier coating
Prior art date
Application number
PCT/EP2009/060387
Other languages
German (de)
French (fr)
Inventor
Thomas Heinz-Schwarzmaier
Thomas Duda
Alexander Schnell
Original Assignee
Alstom Technology Ltd.
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Application filed by Alstom Technology Ltd. filed Critical Alstom Technology Ltd.
Priority to EP09781705.0A priority Critical patent/EP2313615B2/en
Publication of WO2010018174A1 publication Critical patent/WO2010018174A1/en
Priority to US13/024,545 priority patent/US20110171039A1/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
    • 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 gas turbines. It relates to a blade arrangement of a gas turbine according to the preamble of claim 1.
  • the blades 11 which project radially into the hot gas duct 13 of the gas turbine and rotate about the axis 16 terminate in one with one first cover layer 15 provided blade tip 27, which is opposite to a game 25 a the outer wall 26 of the hot gas channel 13 forming heat shield 12, 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 from 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 27 and the heat shield 12 takes into account the different thermal expansions and is 2 B07 / 139-0
  • blade arrangements 20 according to FIG. 2 have been proposed (see, for example, EP-A2-1 312 760 or US-A1- 2008166225) in which the rotor blades are embedded in a carrier layer 19 on the blade tip 27 Grinding elements (grains) 21 (eg made of cubic boron nitride cBN) are arranged, with which the blade tip 27 can grind into operation in an abradable thermal barrier coating 18 (Thermal Barrier Coating TBC) 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. However, the goal would have to be to produce a comparable grinding behavior without having to provide a special grinding layer on the blade tip.
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a blade assembly, which avoids the disadvantages of known blade assemblies and allows a significant reduction in the game between the blade tips and the opposite stator-side elements with a simple design.
  • the heat shield has a porous heat-insulating layer as the outer, abradable layer, and that the blade tip is merely provided with a homogeneous metallic covering layer.
  • Thermal barrier coating allows the blade tip covered with the cover layer to loop into the heat shield without special abrasive particles or abrasive layer and thus to optimally minimize the 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.
  • thermal barrier coating is a porous ceramic layer, in particular of YSZ.
  • porosity of the thermal barrier coating is greater than 20%.
  • an adhesive layer in particular of MCrAIY, is advantageously arranged.
  • the metallic cover layer is preferably made of MCrAIY.
  • Another embodiment is characterized in that the blade is part of the first blade row in the turbine part of the gas turbine.
  • FIG. 1 in a greatly simplified representation of an earlier
  • Blade assembly with a special abrasive layer on the blade tip
  • FIG. 3 shows a preferred exemplary embodiment of a blade arrangement 30 according to the invention.
  • 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-in 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.
  • a thermal barrier coating 23 is a porous ceramic layer, which may consist in particular of YSZ (yttria-stabilized zirconium oxide), wherein the porosity is generated for example by embedded polymers, which are later heated. It has been found 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%.
  • 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.

Abstract

The invention relates to the blade arrangement (30) of a gas turbine with at least one blade (11), which protrudes in the radial direction into a hot gas channel (13) arranged concentrically in relation to an axis (16) and ends in a blade tip (27), which lies opposite, with a clearance (25), a heat shield (12) bounding the hot gas channel (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) are covered with layers (22, 23, 24) that make it possible for the blade tip (27) to grind into the heat shield (12) in a specifically intended manner.  With such a blade arrangement, a reduction in the clearance by allowing grinding-in is achieved in a simplified way by the heat shield (12) having an exterior abradable layer of a porous thermal barrier coating (23), and by the blade tip (27) being provided with a homogeneous metallic covering layer (24).

Description

1 B07/139-0 1 B07 / 139-0
SCHAUFELANORDNUNG EINER GASTURBINESHOVEL ASSEMBLY OF A GAS TURBINE
Technisches GebietTechnical area
Die vorliegende Erfindung bezieht sich auf das Gebiet der Technik der Gasturbinen. Sie betrifft eine Schaufelanordnung einer Gasturbine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbines. It relates to a blade arrangement of a gas turbine 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 2 B07/139-0In the simplest case, as shown in FIG. 1 on the basis of the blade arrangement 10, no special measures are taken to optimize the gap width: The blades 11 which project radially into the hot gas duct 13 of the gas turbine and rotate about the axis 16 terminate in one with one first cover layer 15 provided blade tip 27, which is opposite to a game 25 a the outer wall 26 of the hot gas channel 13 forming heat shield 12, 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 from 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 27 and the heat shield 12 takes into account the different thermal expansions and is 2 B07 / 139-0
daher vergleichsweise gross, um ein Schleifen der Bauteile im Betrieb zu vermeiden.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-A2-1 312 760 oder die US-A1- 2008166225), bei denen an der Schaufelspitze 27 der Laufschaufeln in eine Trägerschicht 19 eingebettet Schleifkörper (Körner) 21 (z.B. aus 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 according to FIG. 2 have been proposed (see, for example, EP-A2-1 312 760 or US-A1- 2008166225) in which the rotor blades are embedded in a carrier layer 19 on the blade tip 27 Grinding elements (grains) 21 (eg made of cubic boron nitride cBN) are arranged, with which the blade tip 27 can grind into operation in an abradable thermal barrier coating 18 (Thermal Barrier Coating TBC) 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. Ziel müsste aber sein, ein vergleichbares Einschleifverhalten zu erzeugen, ohne dass an der Schaufelspitze eine spezielle Schleifschicht vorgesehen werden muss.The abrasive layer 19, 21 of such a blade arrangement is constructed comparatively complex by the embedded abrasive body and therefore expensive to manufacture. However, the goal would have to be to produce a comparable grinding behavior without having to provide a special grinding layer on the blade tip.
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 gleichzeitig einfachem Aufbau eine deutliche Verringerung des Spiels zwischen den Schaufelspitzen und den gegenüberliegenden statorseitigen Elementen ermöglicht.The invention aims to remedy this situation. It is therefore an object of the invention to provide a blade assembly, which avoids the disadvantages of known blade assemblies and allows a significant reduction in the game between the blade tips and the opposite stator-side elements with a simple design.
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 aufweist, und dass die Schaufelspitze lediglich mit einer homogenen metallischen Abdeckschicht versehen ist. Die poröse 3 B07/139-0The object is solved by the entirety of the features of claim 1. It is essential for the invention that the heat shield has a porous heat-insulating layer as the outer, abradable layer, and that the blade tip is merely provided with a homogeneous metallic covering layer. The porous one 3 B07 / 139-0
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.Thermal barrier coating allows the blade tip covered with the cover layer to loop into the heat shield without special abrasive particles or abrasive layer and thus to optimally minimize the 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 Wärmedämmschicht eine poröse Keramikschicht, insbesondere aus YSZ, ist. Vorzugsweise ist dabei die Porosität der Wärmedämmschicht grösser 20 %.Another embodiment of the invention is characterized in that the thermal barrier coating is a porous ceramic layer, in particular 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.
Die metallische Abdeckschicht besteht vorzugsweise aus MCrAIY.The metallic cover layer is preferably made of MCrAIY.
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 zeigenThe invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1 in einer stark vereinfachten Darstellung eine frühereFig. 1 in a greatly simplified representation of an earlier
Schaufelanordnung ohne die Möglichkeit des Einschleifens; 4 B07/139-0Blade arrangement without the possibility of grinding; 4 B07 / 139-0
Fig. 2 in einer zu Fig. 1 vergleichbaren Darstellung eine andere frühereFig. 2 in a comparable to Fig. 1 representation another earlier
Schaufelanordnung mit einer speziellen Schleifschicht auf der Schaufelspitze undBlade assembly with a special abrasive layer on the blade tip and
Fig. 3 in einer zu Fig. 1 vergleichbaren Darstellung eine für dasFig. 3 in a comparable to Fig. 1 representation one for the
Einschleifen vorgesehen Schaufelanordnung mit einer einfachen Abdeckschicht auf der Schaufelspitze gemäss einem Ausführungsbeispiel der Erfindung.Grinding provided 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 drehbare 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).FIG. 3 shows a preferred exemplary embodiment of a blade arrangement 30 according to the invention. 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-in 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 verwendet wird. 5 B07/139-0In 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 heat-insulating layer 23 - without losing their thermal properties - is sufficiently easy to grind. This can be achieved by using a porous thermal barrier coating 23. 5 B07 / 139-0
Besonders geeignet als Wärmedämmschicht 23 ist dabei eine poröse Keramikschicht, die insbesondere aus YSZ (Yttriumoxid-stabilisiertem Zirkoniumoxid) bestehen kann, 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 20 % ist, also beispielsweise im Bereich von 22-24 % liegt.Particularly suitable as a thermal barrier coating 23 is a porous ceramic layer, which may consist in particular of YSZ (yttria-stabilized zirconium oxide), wherein the porosity is generated for example by embedded polymers, which are later heated. It has been found 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.
6 B07/139-06 B07 / 139-0
BezugszeichenlisteLIST OF REFERENCE NUMBERS
10,20.30 Schaufelanordnung (Gasturbine)10.20.30 Blade assembly (gas turbine)
11 Laufschaufel11 blade
12 Hitzeschild12 heat shield
13 Heissgaskanal13 hot gas channel
14,15,24 Abdeckschicht14,15,24 covering layer
16 Achse16 axis
17,22 Haftschicht17.22 adhesive layer
18,23 Wärmedämmschicht (TBC)18,23 thermal barrier coating (TBC)
19 Trägerschicht19 carrier layer
21 Schleifkörper21 grinding wheels
25 Spiel25 game
26 Wand (Heissgaskanal)26 wall (hot gas channel)
27 Schaufelspitze27 bucket tip
28 Einschleifbereich 28 grinding area

Claims

7 B07/139-0Patentansprüche 7 B07 / 139-0Patent claims
1. Schaufelanordnung (30) einer thermischen Strömungsmaschine mit wenigstens einer Schaufel (11 ), welche in radialer Richtung in einen zu einer1. blade assembly (30) of a thermal turbomachine with at least one blade (11), which in the radial direction in one to a
Achse (16) konzentrisch angeordneten Heissgas durchströmten Kanal (13) hineinragt und in einer Schaufelspitze (27) endet, die mit einem Spiel (25) einem den Kanal (13) begrenzenden Hitzeschild (12) gegenüber liegt, wobei die Schaufel (11 ) und der Hitzeschild (12) in Umfangsrichtung relativ zueinander beweglich sind, und die Schaufelspitze (27) und der HitzeschildAxis (16) concentrically arranged hot gas flowed through channel (13) and ends in a blade tip (27) with a game (25) the channel (13) limiting the heat shield (12), wherein the blade (11) and the heat shield (12) are movable relative to each other in the circumferential direction, and the blade tip (27) and the heat shield
(12) mit Schichten (22, 23, 24) bedeckt sind, welche ein gezieltes Einschleifen der Schaufelspitze (27) in den Hitzeschild (12) ermöglichen, dadurch gekennzeichnet, dass der Hitzeschild (12) als äussere, abschleifbare Schicht eine poröse Wärmedämmschicht (23) aufweist, und dass die Schaufelspitze (27) mit einer homogenen metallischen(12) are covered with layers (22, 23, 24), which allow a targeted grinding of the blade tip (27) into the heat shield (12), characterized in that the heat shield (12) as an outer abradable layer, a porous thermal barrier coating (12). 23), and that the blade tip (27) with a homogeneous metallic
Abdeckschicht (24) versehen ist.Cover layer (24) is provided.
2. Schaufelanordnung nach Anspruch 1 , dadurch gekennzeichnet, dass die thermische Strömungsmaschine eine Gasturbine ist, dass die Schaufel eine um die Achse (16) rotierende Laufschaufel (11 ) ist, und dass der Hitzeschild2. Blade assembly according to claim 1, characterized in that the thermal fluid machine is a gas turbine, that the blade is a about the axis (16) rotating blade (11), and that the heat shield
(12) am Stator der Gasturbine ortsfest montiert ist.(12) is fixedly mounted on the stator of the gas turbine.
3. Schaufelanordnung nach Anspruch 1 und/oder 2, dadurch gekennzeichnet, dass die Wärmedämmschicht (23) eine poröse Keramikschicht, insbesondere aus YSZ, ist.3. blade assembly according to claim 1 and / or 2, characterized in that the thermal barrier coating (23) is a porous ceramic layer, in particular of YSZ.
4. Schaufelanordnung nach Anspruch 3, dadurch gekennzeichnet, dass die Porosität der Wärmedämmschicht (23) grösser 20 % ist.4. blade assembly according to claim 3, characterized in that the porosity of the thermal barrier coating (23) is greater than 20%.
5. Schaufelanordnung nach Anspruch 3 oder 4, dadurch gekennzeichnet, das zwischen dem Hitzeschild (12) und der Wärmedämmschicht (23) eine Haftschicht (22), insbesondere aus MCrAIY, angeordnet ist. 8 B07/139-05. blade assembly according to claim 3 or 4, characterized in that between the heat shield (12) and the thermal barrier coating (23) an adhesive layer (22), in particular of MCrAIY, is arranged. 8 B07 / 139-0
6. Schaufelanordnung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die metallische Abdeckschicht (24) aus MCrAIY besteht.6. blade assembly according to one of claims 1 to 5, characterized in that the metallic cover layer (24) consists of MCrAIY.
7. Schaufelanordnung nach Anspruch 2, dadurch gekennzeichnet, dass die Laufschaufel (11 ) Teil der ersten Laufschaufelreihe im Turbinenteil der Gasturbine ist. 7. Blade assembly according to claim 2, characterized in that the moving blade (11) is part of the first blade row in the turbine part of the gas turbine.
PCT/EP2009/060387 2008-08-15 2009-08-11 Blade arrangement of a gas turbine WO2010018174A1 (en)

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EP09781705.0A EP2313615B2 (en) 2008-08-15 2009-08-11 Blade arrangement of a gas turbine
US13/024,545 US20110171039A1 (en) 2008-08-15 2011-02-10 Blade arrangement of a gas turbine

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CH01285/08 2008-08-15

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Also Published As

Publication number Publication date
EP2313615A1 (en) 2011-04-27
US20110171039A1 (en) 2011-07-14
EP2313615B1 (en) 2016-03-23
CH699312A1 (en) 2010-02-15
EP2313615B2 (en) 2023-09-27

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