EP2313615A1 - Schaufelanordnung einer gasturbine - Google Patents
Schaufelanordnung einer gasturbineInfo
- Publication number
- EP2313615A1 EP2313615A1 EP09781705A EP09781705A EP2313615A1 EP 2313615 A1 EP2313615 A1 EP 2313615A1 EP 09781705 A EP09781705 A EP 09781705A EP 09781705 A EP09781705 A EP 09781705A EP 2313615 A1 EP2313615 A1 EP 2313615A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- heat shield
- layer
- blade tip
- barrier coating
- 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.)
- Granted
Links
- 239000012720 thermal barrier coating Substances 0.000 claims abstract description 18
- 239000010410 layer Substances 0.000 claims description 34
- 239000012790 adhesive layer Substances 0.000 claims description 6
- 239000000919 ceramic Substances 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims 1
- 239000007789 gas Substances 0.000 description 16
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 229910052582 BN Inorganic materials 0.000 description 1
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 229910001928 zirconium oxide Inorganic materials 0.000 description 1
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.
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)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH01285/08A CH699312A1 (de) | 2008-08-15 | 2008-08-15 | Schaufelanordnung einer gasturbine. |
PCT/EP2009/060387 WO2010018174A1 (de) | 2008-08-15 | 2009-08-11 | Schaufelanordnung einer gasturbine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2313615A1 true EP2313615A1 (de) | 2011-04-27 |
EP2313615B1 EP2313615B1 (de) | 2016-03-23 |
EP2313615B2 EP2313615B2 (de) | 2023-09-27 |
Family
ID=40090118
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09781705.0A Active EP2313615B2 (de) | 2008-08-15 | 2009-08-11 | Schaufelanordnung einer gasturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20110171039A1 (de) |
EP (1) | EP2313615B2 (de) |
CH (1) | CH699312A1 (de) |
WO (1) | WO2010018174A1 (de) |
Families Citing this family (7)
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 (de) * | 2013-06-28 | 2014-12-31 | Siemens Aktiengesellschaft | Gasturbine und Hitzeschild für eine Gasturbine |
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 |
DE102017207238A1 (de) * | 2017-04-28 | 2018-10-31 | Siemens Aktiengesellschaft | Dichtungssystem für Laufschaufel und Gehäuse |
US11346232B2 (en) * | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
Family Cites Families (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IL75564A (en) * | 1984-06-25 | 1988-02-29 | United Technologies Corp | Abrasive surfaced article for high temperature service |
US4936745A (en) * | 1988-12-16 | 1990-06-26 | United Technologies Corporation | Thin abradable ceramic air seal |
US6102656A (en) * | 1995-09-26 | 2000-08-15 | United Technologies Corporation | Segmented abradable ceramic coating |
US5824423A (en) † | 1996-02-07 | 1998-10-20 | N.V. Interturbine | Thermal barrier coating system and methods |
US6149389A (en) † | 1996-03-13 | 2000-11-21 | Forschungszentrum Karlsruhe Gmbh | Protective coating for turbine blades |
US5883314A (en) * | 1996-06-11 | 1999-03-16 | Sievers; George K. | Coating methods, coating products and coated articles |
US6095755A (en) † | 1996-11-26 | 2000-08-01 | United Technologies Corporation | Gas turbine engine airfoils having increased fatigue strength |
US5733102A (en) † | 1996-12-17 | 1998-03-31 | General Electric Company | Slot cooled blade tip |
US5794338A (en) † | 1997-04-04 | 1998-08-18 | General Electric Company | Method for repairing a turbine engine member damaged tip |
SG72959A1 (en) * | 1998-06-18 | 2000-05-23 | United Technologies Corp | Article having durable ceramic coating with localized abradable portion |
DE19842417A1 (de) † | 1998-09-16 | 2000-03-30 | Coatec Ges Fuer Oberflaechenve | Verfahren zum Herstellen einer Beschichtung gegen Heißgaskorrosion und -oxidation, insbesondere zur Anwendung in Gasturbinen |
US6224337B1 (en) | 1999-09-17 | 2001-05-01 | General Electric Company | Thermal barrier coated squealer tip cavity |
EP1143030A1 (de) † | 2000-04-03 | 2001-10-10 | ABB Alstom Power N.V. | Werkstoff für Turbinenschaufelspitze und dessen Herstellungs-oder Reparierungsverfahren |
DE10140742B4 (de) † | 2000-12-16 | 2015-02-12 | Alstom Technology Ltd. | Vorrichtung zur Dichtspaltreduzierung zwischen einer rotierenden und einer stationären Komponente innerhalb einer axial durchströmten Strömungsmaschine |
US6502304B2 (en) † | 2001-05-15 | 2003-01-07 | General Electric Company | Turbine airfoil process sequencing for optimized tip performance |
FR2832180B1 (fr) | 2001-11-14 | 2005-02-18 | Snecma Moteurs | Revetement abradable pour parois de turbines a gaz |
DE10225532C1 (de) † | 2002-06-10 | 2003-12-04 | Mtu Aero Engines Gmbh | Schichtsystem für die Rotor-/Statordichtung einer Strömungsmaschine |
US6916529B2 (en) † | 2003-01-09 | 2005-07-12 | General Electric Company | High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same |
US7316850B2 (en) † | 2004-03-02 | 2008-01-08 | Honeywell International Inc. | Modified MCrAlY coatings on turbine blade tips with improved durability |
US7378132B2 (en) † | 2004-12-14 | 2008-05-27 | Honeywell International, Inc. | Method for applying environmental-resistant MCrAlY coatings on gas turbine components |
US7510370B2 (en) * | 2005-02-01 | 2009-03-31 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
US7601431B2 (en) * | 2005-11-21 | 2009-10-13 | General Electric Company | Process for coating articles and articles made therefrom |
CA2585992C (en) † | 2006-06-08 | 2014-06-17 | Sulzer Metco (Us) Inc. | Dysprosia stabilized zirconia abradable |
EP1890010B1 (de) † | 2006-08-10 | 2016-05-04 | United Technologies Corporation | Keramische Turbinenmantelanordnung |
US8431238B2 (en) * | 2008-02-19 | 2013-04-30 | Parker-Hannifin Corporation | Protective coating for metallic seals |
US20090324841A1 (en) * | 2008-05-09 | 2009-12-31 | Siemens Power Generation, Inc. | Method of restoring near-wall cooled turbine components |
-
2008
- 2008-08-15 CH CH01285/08A patent/CH699312A1/de not_active Application Discontinuation
-
2009
- 2009-08-11 WO PCT/EP2009/060387 patent/WO2010018174A1/de active Application Filing
- 2009-08-11 EP EP09781705.0A patent/EP2313615B2/de active Active
-
2011
- 2011-02-10 US US13/024,545 patent/US20110171039A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO2010018174A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP2313615B2 (de) | 2023-09-27 |
CH699312A1 (de) | 2010-02-15 |
WO2010018174A1 (de) | 2010-02-18 |
US20110171039A1 (en) | 2011-07-14 |
EP2313615B1 (de) | 2016-03-23 |
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