EP2313615B1 - Blade arrangement of a gas turbine - Google Patents
Blade arrangement of a gas turbine Download PDFInfo
- 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
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- heat shield
- coating
- blade tip
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000012720 thermal barrier coating Substances 0.000 claims description 18
- 238000000576 coating method Methods 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 7
- 238000005524 ceramic coating Methods 0.000 claims 2
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 claims 1
- 229910052727 yttrium Inorganic materials 0.000 claims 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims 1
- 229910001928 zirconium oxide Inorganic materials 0.000 claims 1
- 239000010410 layer Substances 0.000 description 27
- 239000007789 gas Substances 0.000 description 20
- 238000000227 grinding Methods 0.000 description 13
- 239000012790 adhesive layer Substances 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 239000000919 ceramic Substances 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 239000000758 substrate Substances 0.000 description 3
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 description 3
- 229910052582 BN Inorganic materials 0.000 description 2
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 239000003082 abrasive agent Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
Images
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 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.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
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.
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
Um das Spiel 25 reduzieren zu können, sind Schaufelanordnungen 20 gemäss
Die Schleifschicht 19, 21 einer solchen Schaufelanordnung ist durch die eingelagerten Schleifkörper vergleichsweise komplex aufgebaut und daher aufwändig in der Herstellung.The
Dokument
Die Druckschrift
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.
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 frĂĽhere 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.
- 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.
In
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
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
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
Auf diese Weise brauchen an der Schaufel 11 keine besonderen Vorkehrungen fĂĽr 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
- 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)
- 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.
- 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.
- Blade arrangement according to Claim 1 and/or 2, characterized in that the porous ceramic coating consists of YSZ (yttrium oxide-stabilized zirconium oxide).
- Blade arrangement according to Claim 3, characterized in that the porosity of the thermal barrier coating (23) is more than 20%.
- 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).
- 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.
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 |
Family
ID=40090118
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 |
Country Status (4)
Country | Link |
---|---|
US (1) | US20110171039A1 (en) |
EP (1) | EP2313615B2 (en) |
CH (1) | CH699312A1 (en) |
WO (1) | WO2010018174A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102017207238A1 (en) * | 2017-04-28 | 2018-10-31 | Siemens Aktiengesellschaft | Sealing system for blade and housing |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130186304A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Process of fabricating a thermal barrier coating and an article having a cold sprayed thermal barrier coating |
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 |
US10864447B1 (en) | 2015-06-29 | 2020-12-15 | Amazon Technologies, Inc. | Highlight presentation interface in a game spectating system |
US11346232B2 (en) * | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
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US7510370B2 (en) * | 2005-02-01 | 2009-03-31 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
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2008
- 2008-08-15 CH CH01285/08A patent/CH699312A1/en not_active Application Discontinuation
-
2009
- 2009-08-11 EP EP09781705.0A patent/EP2313615B2/en active Active
- 2009-08-11 WO PCT/EP2009/060387 patent/WO2010018174A1/en active Application Filing
-
2011
- 2011-02-10 US US13/024,545 patent/US20110171039A1/en not_active Abandoned
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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 |
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WO2010018174A1 (en) | 2010-02-18 |
CH699312A1 (en) | 2010-02-15 |
EP2313615A1 (en) | 2011-04-27 |
US20110171039A1 (en) | 2011-07-14 |
EP2313615B2 (en) | 2023-09-27 |
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