WO2005071228A1 - Schichtsystem für eine rotor-/ statordichtung einer strömungsmaschine - Google Patents
Schichtsystem für eine rotor-/ statordichtung einer strömungsmaschine Download PDFInfo
- Publication number
- WO2005071228A1 WO2005071228A1 PCT/DE2004/002815 DE2004002815W WO2005071228A1 WO 2005071228 A1 WO2005071228 A1 WO 2005071228A1 DE 2004002815 W DE2004002815 W DE 2004002815W WO 2005071228 A1 WO2005071228 A1 WO 2005071228A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- layer
- inlet
- layers
- layer system
- rotor
- Prior art date
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
- F05D2300/2118—Zirconium oxides
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/506—Hardness
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the invention relates to a layer system for a rotor / stator seal of a turbomachine, in particular a gas turbine, according to the preamble of claim 1. Furthermore, the invention relates to a turbomachine with such a rotor / stator seal.
- a gas turbine such as an aircraft engine, has at least one rotor and at least one stator.
- Several rotor blades rotating together with the rotor are assigned to the rotor, the rotor blades rotating relative to a stator.
- the stator is usually formed by a fixed housing and fixed guide vanes.
- the gap dimension of the above column is not constant, but is subject to changes during the different operating phases of the gas turbine.
- the rotating blades experience an elongation in the radial direction under high operating loads due to the thermal stress and the acting centrifugal force, while the stator-side, fixed housing is only subjected to thermal expansion.
- inlet linings i.e. Pads with low abrasion resistance
- Inlet coverings with low abrasion resistance also have good thermal insulation and, due to their good infeed ability, allow inlet depths in the millimeter range (typically 0.1 mm to 1.0 mm) without damaging the blades.
- Such an inlet covering is known for example from US 4,936,745.
- a layer system for a rotor / stator seal of a turbomachine, which is applied to a metallic component, is known from the unpublished DE 102 25 532.
- the metallic component is, for example, a housing made of a titanium-based alloy.
- the layer system described there can be run-in compared to a rotating component and has a two-layer run-in coating.
- the two layers of the inlet covering are ceramic, a first, inner layer of the inlet covering being relatively hard and a second, outer layer being able to enter.
- the two layers of the layer system according to DE 102 25 532 both have a constant consistency along their thickness, so they are both not graded.
- the present invention is based on the problem of proposing a novel layer system for the rotor / stator seal of a turbomachine and a corresponding turbomachine.
- This problem is solved in that the above-mentioned layer system for the rotor / stator seal of a turbomachine is further developed by the features of the characterizing part of patent claim 1.
- the layers of the inlet covering are each graded such that the porosity and / or composition thereof changes over the thickness of the layers, the first, inner layer of the inlet covering having a lower porosity relative to the second, outer layer of the inlet covering and / or is denser, and wherein the first, inner layer of the run-in covering provides a titanium fire protection layer.
- the layer system according to the invention has an at least two-layer inlet covering, all layers of the inlet covering being graded in such a way that the porosity and / or composition of the layers changes over the thickness thereof.
- the layer system is specially designed for rotors and stators that are made of a titanium-based alloy or a titanium-aluminum alloy.
- the inner layer of the inlet covering provides a titanium fire protection layer. With such a titanium fire protection layer, a titanium fire on the components made of the titanium-based alloy or the titanium-aluminum alloy can be reliably prevented.
- the second, outer layer is both shrinkable and erosion-resistant.
- the run-in covering has three layers, a third layer being arranged between the first, inner layer and the second, outer layer, and all three layers being graded such that the porosity and / or composition changed.
- the third layer preferably provides a thermal barrier coating.
- a metallic adhesive layer is preferably arranged between the first component and the inlet lining, the adhesive layer being arranged between the first, inner layer of the inlet lining and the component.
- FIG. 1 shows a highly schematic basic diagram to illustrate the problem on which the present invention is based
- FIG. 2 shows a schematic representation of the layer system according to the invention
- FIG. 3 shows a cross section through a layer system according to the invention in a so-called bright field representation
- FIG. 4 shows a cross section through the layer system according to the invention from FIG. 3 in a so-called dark field representation.
- Fig. 1 shows a highly schematic of a rotating blade 10 of a gas turbine, which rotates in the direction of arrow 12 relative to a stationary, stator-side housing 11.
- a layer system 13 for a rotor / stator seal is arranged on the housing 11 between the rotor-side rotor blade 10 and the stator-side housing 11, the layer system 13 forming an inlet lining.
- the layer system 13 serves to seal a radial gap between a tip 14 of the rotating rotor blade 10 and the stationary housing 11.
- the housing 11 shown schematically in FIG. 1 is the housing of a compressor according to the preferred embodiment.
- the requirements placed on such a layer system are very complex.
- the layer system must have an optimized abrasion behavior, ie good chip formation and removal of the abrasion must be guaranteed. Furthermore, no material transfer to the rotating blades 10 may take place.
- the layer system 13 must also have a low frictional resistance when rubbed in. Furthermore, the layer system 13 must not ignite when touched by the rotating blades 10.
- a housing 1 which is preferably made of a titanium base alloy or a titanium-aluminum alloy or another material is formed, and in the case of blades 10 which are formed from a titanium-based alloy or a titanium-aluminum alloy, a titanium fire must be reliably avoided.
- FIG. 1 illustrates that, due to the centrifugal forces that occur during operation of the gas turbine and the heating of the gas turbine, the ends 14 of the rotor blades 10 come into contact with the layer system 13 and so an abrasion 15 is released. This pulverized abrasion 15 must not cause any damage to the rotating blades 10.
- a layer system for a rotor / stator seal of a turbomachine, preferably a gas turbine, is now proposed, which is based on a first component, namely on the housing 11, which is preferably made of a titanium-based alloy or a titanium-aluminum alloy is formed, is applied.
- Fig. 2 shows a particularly preferred embodiment of this layer system, which is applied to the housing 1 1.
- the layer system according to FIG. 2 has an inlet covering 13, the inlet covering 13 in the exemplary embodiment of FIG. 2 being formed from three layers, namely from a first, inner layer 16, a second, outer layer 17 and one between the two layers 16 and 17 arranged third layer 18. It should be noted that the third layer 18 is optional, but particularly preferred.
- all three layers 16, 17 and 18 of the inlet covering 13 are ceramic. All three layers 16, 17 and 18 of the run-in coating 13 are preferably formed from a zirconium oxide partially stabilized with 6-8% by weight of yttrium oxide, preferably from Zr0 2 -7Y 2 0 3 . Furthermore, all three layers 16, 17 and 18 of the inlet covering 13 are graded in such a way that the porosity and / or composition thereof changes over the thickness of the layers 16, 17 and 18.
- the first, inner layer 16 of the inlet lining 13 is relatively hard and relatively dense compared to the second, outer layer 17 and accordingly has a relatively low porosity.
- the first, inner layer 16 forms a titanium fire protection layer.
- the second, outer layer 17 of the inlet covering 13 is relatively soft and has a relatively large porosity.
- the second, outer layer 17 is capable of being run in and allows the tips 14 of the rotating rotor blades 10 to run into the run-in coating 13 without wear.
- the third layer 18 positioned between the two layers 16 and 17 provides a thermal insulation layer and forms a transition between the layers 16 and 16 17th
- an adhesive layer 19 is arranged between the inlet covering 13 and the housing 11. 2
- the adhesive layer 19 is arranged between the first, inner layer 16 of the inlet covering 13 and the housing 11.
- the adhesive layer is metallic, preferably made of a nickel-aluminum alloy.
- the adhesive layer 19 has a rough surface which is matched to the first, inner layer 16 of the inlet covering 13 in order to interlock with the first, inner layer 16 of the inlet covering 13 and good adhesion of the inlet covering 13 to the adhesive layer 19 and thus ultimately to ensure on the housing 1 1.
- FIGS. 3 and 4 show microscopic images of a layer system according to the invention, FIG. 3 being a so-called bright field representation and FIG. 4 being a so-called dark field representation.
- the different porosity of the graded layers 16, 17 and 18 of the inlet covering 13 can be seen from the representations of FIGS. 3 and 4.
- the entire inlet covering 13 typically has a thickness of 1.0 mm to 10 mm, in particular a thickness of 1.5 mm to 5 mm, particularly preferably a thickness of 1.5 mm to 3 mm.
- the first, inner layer 16 of the inlet covering 13 has a thickness of at least 1 mm. 4 shows that in the preferred exemplary embodiment the first, inner layer 16 has a thickness of 1000 ⁇ m, that is to say 1 mm.
- the second, outer layer 17 has a thickness of at least 0.4 mm, in particular of at least 0.8 mm because of the inlet depths to be guaranteed. 4, the second, outer layer 17 has a thickness of 1050 ⁇ m, that is 1.05 mm.
- the third layer 18 positioned between the first inner layer 16 and the second outer layer 17 has a thickness of at least 0.1 mm, in particular a thickness of at least 0.3 mm. 4, the thickness of the third layer is 330 ⁇ m, that is 0.33 mm.
- Each of the graded ceramic layers 16, 17 and 18 of the run-in coating 13 is produced by thermal spraying.
- the grading can be achieved, for example, by changing the ratio of the materials used for thermal spraying during the application of one of the layers 16, 17 and 18.
- process parameters such as the process temperature, can be changed during thermal spraying in order to influence the porosity. This can also influence the porosity.
- a layer system for a rotor / stator seal of a turbomachine which has a multilayer inlet coating, each layer of the inlet coating being ceramic and having a graded, i.e. continuously changing, porosity and / or composition.
- the fact that ceramic layers are used throughout in the inlet covering means that leaps in properties within the inlet covering are reduced to a minimum. This increases the lifespan of the running-in covering.
- the running-in covering according to the invention simultaneously fulfills requirements such as titanium fire protection, erosion resistance, good abrasion behavior and thermal insulation. It is particularly suitable for use in an aircraft engine compressor.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Inorganic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Ceramic Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004002943.1 | 2004-01-21 | ||
DE102004002943A DE102004002943B4 (de) | 2004-01-21 | 2004-01-21 | Schichtsystem für eine Rotor-/Statordichtung einer Strömungsmaschine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005071228A1 true WO2005071228A1 (de) | 2005-08-04 |
Family
ID=34744924
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2004/002815 WO2005071228A1 (de) | 2004-01-21 | 2004-12-24 | Schichtsystem für eine rotor-/ statordichtung einer strömungsmaschine |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE102004002943B4 (de) |
WO (1) | WO2005071228A1 (de) |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007112783A1 (de) * | 2006-04-06 | 2007-10-11 | Siemens Aktiengesellschaft | Layered thermal barrier coating with a high porosity, and a component |
DE102008019296A1 (de) | 2008-04-16 | 2009-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zur Herstellung eines Feuerschutzes für aus Titan bestehende Bauteilkörper einer Fluggasturbine und Bauteilkörper aus Titan für eine Fluggasturbine |
WO2010026180A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur |
US7871244B2 (en) | 2007-02-15 | 2011-01-18 | Siemens Energy, Inc. | Ring seal for a turbine engine |
US8105014B2 (en) | 2009-03-30 | 2012-01-31 | United Technologies Corporation | Gas turbine engine article having columnar microstructure |
EP2428593A1 (de) * | 2010-09-14 | 2012-03-14 | United Technologies Corporation | Abreibbare Beschichtung mit Sicherheitssicherung |
EP2905426A1 (de) * | 2014-02-11 | 2015-08-12 | Siemens Aktiengesellschaft | Komponente mit einer abschleifbaren Beschichtung und Verfahren zur Beschichtung der abschleifbaren Beschichtung |
US9316110B2 (en) | 2013-08-08 | 2016-04-19 | Solar Turbines Incorporated | High porosity abradable coating |
EP2439379A3 (de) * | 2010-10-11 | 2017-07-12 | MTU Aero Engines AG | Schichtsystem zur Rotor-/Statordichtung einer Strömungsmaschine und Verfahren zum Herstellen eines derartigen Schichtsystems |
EP3239467A1 (de) * | 2016-04-27 | 2017-11-01 | Siemens Aktiengesellschaft | Strömungsmaschine, laufschaufel und gehäuse |
RU177607U1 (ru) * | 2017-08-22 | 2018-03-02 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Корпус компрессора газотурбинного двигателя |
RU182167U1 (ru) * | 2017-08-22 | 2018-08-06 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Ротор компрессора газотурбинного двигателя |
CN110573696A (zh) * | 2017-04-28 | 2019-12-13 | 西门子股份公司 | 用于转子叶片和壳体的密封系统 |
US10808308B2 (en) * | 2016-06-08 | 2020-10-20 | Mitsubishi Heavy Industries, Ltd. | Thermal barrier coating, turbine member, and gas turbine |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4269903A (en) * | 1979-09-06 | 1981-05-26 | General Motors Corporation | Abradable ceramic seal and method of making same |
US4481237A (en) * | 1981-12-14 | 1984-11-06 | United Technologies Corporation | Method of applying ceramic coatings on a metallic substrate |
EP0765951A2 (de) * | 1995-09-26 | 1997-04-02 | United Technologies Corporation | Verschleissfeste keramische Beschichtung |
EP0965730A2 (de) * | 1998-06-18 | 1999-12-22 | United Technologies Corporation | Gegenstand mit einer abriebesten Beschichtung sowie mit einer örtlich abreibbaren Beschichtung |
US20030211354A1 (en) * | 1996-12-10 | 2003-11-13 | Siemens Westinghouse Power Corporation | Sinter resistant abradable thermal barrier coating |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10225532C1 (de) * | 2002-06-10 | 2003-12-04 | Mtu Aero Engines Gmbh | Schichtsystem für die Rotor-/Statordichtung einer Strömungsmaschine |
-
2004
- 2004-01-21 DE DE102004002943A patent/DE102004002943B4/de not_active Expired - Fee Related
- 2004-12-24 WO PCT/DE2004/002815 patent/WO2005071228A1/de active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4269903A (en) * | 1979-09-06 | 1981-05-26 | General Motors Corporation | Abradable ceramic seal and method of making same |
US4481237A (en) * | 1981-12-14 | 1984-11-06 | United Technologies Corporation | Method of applying ceramic coatings on a metallic substrate |
EP0765951A2 (de) * | 1995-09-26 | 1997-04-02 | United Technologies Corporation | Verschleissfeste keramische Beschichtung |
US20030211354A1 (en) * | 1996-12-10 | 2003-11-13 | Siemens Westinghouse Power Corporation | Sinter resistant abradable thermal barrier coating |
EP0965730A2 (de) * | 1998-06-18 | 1999-12-22 | United Technologies Corporation | Gegenstand mit einer abriebesten Beschichtung sowie mit einer örtlich abreibbaren Beschichtung |
Cited By (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007112783A1 (de) * | 2006-04-06 | 2007-10-11 | Siemens Aktiengesellschaft | Layered thermal barrier coating with a high porosity, and a component |
US7871244B2 (en) | 2007-02-15 | 2011-01-18 | Siemens Energy, Inc. | Ring seal for a turbine engine |
DE102008019296A1 (de) | 2008-04-16 | 2009-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zur Herstellung eines Feuerschutzes für aus Titan bestehende Bauteilkörper einer Fluggasturbine und Bauteilkörper aus Titan für eine Fluggasturbine |
EP2112248A1 (de) | 2008-04-16 | 2009-10-28 | Rolls-Royce Deutschland Ltd & Co KG | Verfahren zur Herstellung eines Feuerschutzes für aus Titan bestehende Bauteilkörper einer Fluggasturbine und Bauteilkörper aus Titan für eine Fluggasturbine |
US8662838B2 (en) | 2008-09-05 | 2014-03-04 | Snecma | Compressor housing resistant to titanium fire, high-pressure compressor including such a housing and aircraft engine fitted with such a compressor |
CN102144100A (zh) * | 2008-09-05 | 2011-08-03 | 斯奈克玛公司 | 耐钛火的压缩机壳体、包括这种壳体的高压压缩机以及安装有这种压缩机的飞行器发动机 |
US20110236192A1 (en) * | 2008-09-05 | 2011-09-29 | Snecma | Compressor housing resistant to titanium fire, high-pressure compressor including such a housing and aircraft engine fitted with such a compressor |
WO2010026180A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur |
RU2524782C2 (ru) * | 2008-09-05 | 2014-08-10 | Снекма | Корпус компрессора, обладающий стойкостью к титановым пожарам, компрессор высокого давления, содержащий такой корпус, и двигатель летательного аппарата, оборудованный таким компрессором |
FR2935764A1 (fr) * | 2008-09-05 | 2010-03-12 | Snecma | Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur |
US8105014B2 (en) | 2009-03-30 | 2012-01-31 | United Technologies Corporation | Gas turbine engine article having columnar microstructure |
EP2428593A1 (de) * | 2010-09-14 | 2012-03-14 | United Technologies Corporation | Abreibbare Beschichtung mit Sicherheitssicherung |
US8727712B2 (en) | 2010-09-14 | 2014-05-20 | United Technologies Corporation | Abradable coating with safety fuse |
EP2439379A3 (de) * | 2010-10-11 | 2017-07-12 | MTU Aero Engines AG | Schichtsystem zur Rotor-/Statordichtung einer Strömungsmaschine und Verfahren zum Herstellen eines derartigen Schichtsystems |
US9316110B2 (en) | 2013-08-08 | 2016-04-19 | Solar Turbines Incorporated | High porosity abradable coating |
EP2905426A1 (de) * | 2014-02-11 | 2015-08-12 | Siemens Aktiengesellschaft | Komponente mit einer abschleifbaren Beschichtung und Verfahren zur Beschichtung der abschleifbaren Beschichtung |
WO2015121008A1 (en) * | 2014-02-11 | 2015-08-20 | Siemens Aktiengesellschaft | Component with an abradable coating and a method for coating the abradable coating |
EP3239467A1 (de) * | 2016-04-27 | 2017-11-01 | Siemens Aktiengesellschaft | Strömungsmaschine, laufschaufel und gehäuse |
US10808308B2 (en) * | 2016-06-08 | 2020-10-20 | Mitsubishi Heavy Industries, Ltd. | Thermal barrier coating, turbine member, and gas turbine |
CN110573696A (zh) * | 2017-04-28 | 2019-12-13 | 西门子股份公司 | 用于转子叶片和壳体的密封系统 |
US11274560B2 (en) | 2017-04-28 | 2022-03-15 | Siemens Energy Global GmbH & Co. KG | Sealing system for a rotor blade and housing |
RU177607U1 (ru) * | 2017-08-22 | 2018-03-02 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Корпус компрессора газотурбинного двигателя |
RU182167U1 (ru) * | 2017-08-22 | 2018-08-06 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Ротор компрессора газотурбинного двигателя |
Also Published As
Publication number | Publication date |
---|---|
DE102004002943A1 (de) | 2005-08-11 |
DE102004002943B4 (de) | 2007-07-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1375696B1 (de) | Schichtsystem für die Rotor-/Statordichtung einer Strömungsmaschine | |
DE102004002943B4 (de) | Schichtsystem für eine Rotor-/Statordichtung einer Strömungsmaschine | |
EP1320662B1 (de) | Dichtungsanordnung | |
DE60122550T2 (de) | Nachgiebiges zwischenstück für eine fanschaufel | |
EP1741876B1 (de) | Schaufel einer Turbomaschine mit einer Schaufelspitzenpanzerung | |
EP1766193B1 (de) | Einlaufbelag | |
WO2006069817A1 (de) | Anordnung zur abdichtung eines spaltes zwischen einem ersten bauteil und einem zweiten bauteil | |
EP3054106B1 (de) | Gasturbinenbauteil | |
WO2000070193A1 (de) | Strömungsmaschine mit einem dichtsystem für einen rotor | |
WO2013026870A1 (de) | Strömungsmaschine mit beschichteter laufschaufelspitze und beschichtetem innengehäuse | |
EP2044293A1 (de) | Gasturbine mit einem mantelringsegment umfassend einen rezirkulationskanal | |
DE102016222720A1 (de) | Dichtungssystem für eine axiale Strömungsmaschine und axiale Strömungsmaschine | |
EP1951992A1 (de) | Schaufel einer turbomaschine | |
DE102016201523A1 (de) | Schaufel einer Strömungsmaschine mit Schaufelfusswärmedämmung | |
EP1654441B1 (de) | Einlaufbelag für Gasturbinen und Verfahren zur Herstellung dieses Einlaufbelags | |
EP1625283B1 (de) | Einlaufbelag für gasturbinen | |
DE102010048147B4 (de) | Schichtsystem zur Rotor-/Statordichtung einer Strömungsmaschine und Verfahren zum Herstellen eines derartigen Schichtsystems | |
DE102004001722A1 (de) | Turbomaschinenschaufel und Verfahren zur Herstellung einer Schaufelspitzenpanzerung an Turbomaschinenschaufeln | |
EP4202219A1 (de) | Bremsvorrichtung für eine windenergieanlage und verfahren zur erhöhung der verschleiss-festigkeit und minimierung des bremsstaubanfalls bei einer derartigen bremsvorrichtung | |
EP2684982A1 (de) | Schutzschicht für eine Komponente einer Strömungsmaschine | |
EP2994616B1 (de) | Anstreifdichtung und dichtungsanordnung | |
DE102022116105A1 (de) | Dichtung für einen Radialspalt | |
EP1892443A1 (de) | Bürstendichtung | |
WO2009138062A2 (de) | Schutzschicht und verfahren zum aufbringen einer schutzschicht | |
EP2218947A1 (de) | Rotor für eine Strömungsmaschine mit einer Wellendichtung und Verfahren zur Reparatur des Rotors |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
122 | Ep: pct application non-entry in european phase |