EP2904211A1 - Surface modifiée autour d'un trou - Google Patents
Surface modifiée autour d'un trouInfo
- Publication number
- EP2904211A1 EP2904211A1 EP13786472.4A EP13786472A EP2904211A1 EP 2904211 A1 EP2904211 A1 EP 2904211A1 EP 13786472 A EP13786472 A EP 13786472A EP 2904211 A1 EP2904211 A1 EP 2904211A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- hole
- layer
- depression
- layer system
- blade
- 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.)
- Withdrawn
Links
- 239000000758 substrate Substances 0.000 claims description 10
- 239000000919 ceramic Substances 0.000 claims description 7
- 238000004901 spalling Methods 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 28
- 238000002485 combustion reaction Methods 0.000 description 17
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 11
- 239000007789 gas Substances 0.000 description 11
- 239000012720 thermal barrier coating Substances 0.000 description 10
- 238000000576 coating method Methods 0.000 description 9
- 238000001816 cooling Methods 0.000 description 8
- 229910017052 cobalt Inorganic materials 0.000 description 6
- 239000010941 cobalt Substances 0.000 description 6
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 6
- 229910000601 superalloy Inorganic materials 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 5
- 239000000956 alloy Substances 0.000 description 5
- 239000013078 crystal Substances 0.000 description 5
- 239000011241 protective layer Substances 0.000 description 5
- 238000005260 corrosion Methods 0.000 description 4
- 229910052759 nickel Inorganic materials 0.000 description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 3
- 239000000292 calcium oxide Substances 0.000 description 3
- ODINCKMPIJJUCX-UHFFFAOYSA-N calcium oxide Inorganic materials [Ca]=O ODINCKMPIJJUCX-UHFFFAOYSA-N 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005566 electron beam evaporation Methods 0.000 description 3
- 229910052735 hafnium Inorganic materials 0.000 description 3
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 3
- 239000000395 magnesium oxide Substances 0.000 description 3
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 3
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 229910052710 silicon Inorganic materials 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 229910052727 yttrium Inorganic materials 0.000 description 3
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 3
- BRPQOXSCLDDYGP-UHFFFAOYSA-N calcium oxide Chemical compound [O-2].[Ca+2] BRPQOXSCLDDYGP-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000007750 plasma spraying Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000009419 refurbishment Methods 0.000 description 2
- 238000005488 sandblasting Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- YPFNIPKMNMDDDB-UHFFFAOYSA-K 2-[2-[bis(carboxylatomethyl)amino]ethyl-(2-hydroxyethyl)amino]acetate;iron(3+) Chemical compound [Fe+3].OCCN(CC([O-])=O)CCN(CC([O-])=O)CC([O-])=O YPFNIPKMNMDDDB-UHFFFAOYSA-K 0.000 description 1
- 241000191291 Abies alba Species 0.000 description 1
- OYPRJOBELJOOCE-UHFFFAOYSA-N Calcium Chemical compound [Ca] OYPRJOBELJOOCE-UHFFFAOYSA-N 0.000 description 1
- 241000251131 Sphyrna Species 0.000 description 1
- 239000008186 active pharmaceutical agent Substances 0.000 description 1
- 239000002318 adhesion promoter Substances 0.000 description 1
- 239000012790 adhesive layer Substances 0.000 description 1
- 239000011449 brick Substances 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 210000003608 fece Anatomy 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 238000012958 reprocessing Methods 0.000 description 1
- 229910052706 scandium Inorganic materials 0.000 description 1
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/30—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer formed with recesses or projections, e.g. hollows, grooves, protuberances, ribs
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D5/005—Repairing methods or devices
-
- 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
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2603/00—Vanes, blades, propellers, rotors with blades
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
-
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/313—Layer deposition by physical vapour deposition
-
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/314—Layer deposition by chemical vapour deposition
-
- 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
- F05D2230/80—Repairing, retrofitting or upgrading methods
-
- 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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/15—Rare earth metals, i.e. Sc, Y, lanthanides
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
-
- 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
-
- 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
- F05D2300/2112—Aluminium 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/607—Monocrystallinity
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/615—Filler
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
-
- 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 the modification of a surface around a hole in a layer system.
- Layer systems are used in particular for components that are used at high temperatures. These are in ⁇ particular turbine blades with a metallic substrate, metallic bonding layer and ceramic thermal barrier coating.
- gas turbine components are cooled by a cooling medium emerges from a cooling hole to cool the component inside, but also to protect the component from the outside of hot gases.
- Such holes are often introduced after complete coating of the substrate, the opening on its inner surface then being a weak point or starting point for crack growth.
- FIGS. 1, 2 show a cooling hole according to the prior art
- FIGS. 3 to 5 embodiments of the invention
- FIG. 6 shows a turbine blade
- FIG. 7 shows a combustion chamber
- FIG 8 is a list of superalloys. The description and the figures represent only embodiments of the invention.
- FIG. 1 shows a plan view of a surface 42 of FIG
- the film cooling hole 13 may have a radial bore 16 with a symmetrical or asymmetrical cross section.
- the film ⁇ cooling hole 13 is formed with a diffuser 19th
- the diffuser 19 is a broadening of the lower portion 16 of the hole 13 (Fig. 2).
- FIG. 2 shows a cross section through a layer system 25.
- the layer system 25 has a substrate 4.
- the substrate 4 is preferably metallic and most particularly comprises nickel- or cobalt-based superalloys.
- alloys according to FIG. 8 are preferably used.
- Anbin- dung 7 is an outer ceramic layer positioned ⁇ introduced 10 having the outermost surface of the 42nd
- a hole 13 is present, which may also have a diffuser 19 on the surface 42.
- Figure 3 shows in plan view the diffuser 19 or the hole 13. With 48, the location in the interface between ceramic
- the diffuser 19 is not surrounded by the recess 51.
- the recess 51 is bent, preferably pliers-shaped or O-shaped. As seen in the overflow direction 60, the ends 54, 57 of the depression 51 also represent the end of the depression 51 seen in the overflow direction 60.
- the recess 51 is here round, oval or bent and can not touch the hole 13 or the diffuser 19 (FIG. 3) or touch and pass into this hole 13, as shown in FIG. the recess 51 is interrupted only by the hole 13 or has a small distance 60 ', 60' 'to the opening of the hole 13. Small here means ⁇ 10% of the length of the recess 51.
- FIG. 4 shows a cross-section through FIG. 2 or also through FIG. 5, where 48 shows the region of the interface between ceramic layer and substrate 4 or adhesion promoter layer 7, which begins at the hole 13 and the depression 51, seen in the flow direction behind the area 48 lies.
- the recess 51 thus extends over the hole 13th
- the TBC 10 breaks off from the cooling-air hole 13
- the TBC only breaks off to the depression 51 and a crack does not extend beyond the depression 51, as viewed in the flow direction.
- the recess 51 extends for the most part over the thickness of the outermost layer 10.
- 6 shows a perspective view of a rotor blade 120 or guide vane show ⁇ 130 of a turbomachine, which extends along a longitudinal axis of the 121st
- the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
- the blade 120, 130 has, along the longitudinal axis 121, a fastening area 400, an adjacent blade platform 403 and an airfoil 406 and a blade tip 415.
- the blade 130 may have at its blade tip ⁇ 415 another platform (not shown).
- a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
- the blade root 183 is, for example, as a hammerhead out staltet ⁇ .
- Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
- the blade 120, 130 has for a medium which flows past the scene ⁇ felblatt 406, a leading edge 409 and a trailing edge 412.
- Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
- the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof. Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
- Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
- These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
- dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece be ⁇ is made of a single crystal.
- a columnar grain structure columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified
- a monocrystalline structure ie the whole workpiece be ⁇ is made of a single crystal.
- directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
- the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co),
- Nickel (Ni) is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf)).
- Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
- the density is preferably 95% of the theoretical
- the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
- nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1 are also preferably used , 5Re.
- thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
- the thermal barrier coating covers the entire MCrAlX layer.
- Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
- the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
- the thermal barrier coating is therefore preferably more porous than the
- Refurbishment means that components 120, 130 may have to be freed of protective layers after use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. Thereafter, a the coating of the component 120, 130 and a renewed use of the component 120, 130.
- the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.
- FIG. 9 shows a combustion chamber 110 of a gas turbine.
- the combustion chamber 110 is configured, for example, as so-called an annular combustion chamber, in which a plurality of in the circumferential direction about an axis of rotation 102 arranged burners 107 open into a common combustion chamber space 154 and generate flames 156th
- the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
- the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
- the combustion chamber wall 153 is provided on its side facing the medium M, Anlagenme- facing side with a formed from heat shield elements 155. liner.
- Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
- M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or
- ceramic heat may be medämm harsh, consisting for example of ZrO 2, ZrO 2 Y203-ie, it is not partially full text or ⁇ dig stabilized by yttrium oxide and / or calcium and / or magnesium oxide.
- Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
- the heat insulating layer can ⁇ ner to have better thermal shock resistance porous, micro- or macro-cracked pERSonal.
- Reprocessing means that heat shield elements may need to be removed 155 after use of protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired.
- the heat shield elements 155 are then, for example, hollow and may still have cooling holes (not shown) which open into the combustion chamber space 154.
- FIG. 10 shows by way of example a gas turbine 100 in a longitudinal partial section.
- the gas turbine 100 has a rotatably mounted about a rotational axis 102 ⁇ rotor 103 having a shaft 101, which is also referred to as the turbine rotor.
- a compressor 105 for example, a torus-like
- Combustion chamber 110 in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
- the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
- annular annular hot gas channel 111 for example.
- turbine stages 112 connected in series form the turbine 108.
- Each turbine stage 112 is formed, for example, from two blade rings . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
- the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
- Coupled to the rotor 103 is a generator or work machine (not shown).
- air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
- the 105 ⁇ be compressed air provided at the turbine end of the compressor is ge ⁇ leads to the burners 107, where it is mixed with a fuel.
- the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
- the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
- the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
- the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
- the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
- substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
- the components in particular for the turbine blade or vane 120, 130 and components of the combustion chamber 110.
- iron-, nickel- or cobalt-based superalloys are used.
- Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
- the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
- M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
- X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium.
- Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
- MCrAlX may still be present a thermal barrier coating, and consists for example of Zr02, Y203-Zr02, ie it is not, partially or completely stabilized by Ytt ⁇ riumoxid and / or calcium oxide and / or magnesium oxide.
- Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
- the guide blade 130 has a guide blade foot facing the inner housing 138 of the turbine 108 (not shown here). ) and a vane head opposite the vane root.
- the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Transducers For Ultrasonic Waves (AREA)
- Analysing Materials By The Use Of Radiation (AREA)
- Polishing Bodies And Polishing Tools (AREA)
Abstract
L'invention concerne une surface modifiée autour d'un trou. Le recours à des creux dans une couche permet d'éviter des craquelures à l'intérieur de l'interface à travers les couches.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13786472.4A EP2904211A1 (fr) | 2012-11-16 | 2013-11-05 | Surface modifiée autour d'un trou |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12192931.9A EP2733310A1 (fr) | 2012-11-16 | 2012-11-16 | Surface modifiée autour d'un trou |
EP13786472.4A EP2904211A1 (fr) | 2012-11-16 | 2013-11-05 | Surface modifiée autour d'un trou |
PCT/EP2013/073001 WO2014075947A1 (fr) | 2012-11-16 | 2013-11-05 | Surface modifiée autour d'un trou |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2904211A1 true EP2904211A1 (fr) | 2015-08-12 |
Family
ID=47189780
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12192931.9A Withdrawn EP2733310A1 (fr) | 2012-11-16 | 2012-11-16 | Surface modifiée autour d'un trou |
EP13786472.4A Withdrawn EP2904211A1 (fr) | 2012-11-16 | 2013-11-05 | Surface modifiée autour d'un trou |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12192931.9A Withdrawn EP2733310A1 (fr) | 2012-11-16 | 2012-11-16 | Surface modifiée autour d'un trou |
Country Status (6)
Country | Link |
---|---|
US (1) | US20160281511A1 (fr) |
EP (2) | EP2733310A1 (fr) |
JP (1) | JP2015536406A (fr) |
CN (1) | CN104797783A (fr) |
IN (1) | IN2015DN03152A (fr) |
WO (1) | WO2014075947A1 (fr) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2015077755A1 (fr) * | 2013-11-25 | 2015-05-28 | United Technologies Corporation | Structure à multiples parois refroidie par film ayant une ou plusieurs indentations |
WO2016105327A1 (fr) * | 2014-12-22 | 2016-06-30 | Siemens Aktiengesellschaft | Procédé permettant de contrôler le délaminage de revêtement entraîné lors de la formation des trous de refroidissement au travers des revêtements de barrière thermique |
US10132166B2 (en) * | 2015-02-27 | 2018-11-20 | General Electric Company | Engine component |
US10024169B2 (en) | 2015-02-27 | 2018-07-17 | General Electric Company | Engine component |
US10094232B2 (en) * | 2015-08-13 | 2018-10-09 | United Technologies Corporation | Self crystalline orientation for increased compliance |
SG11202008268RA (en) | 2018-03-19 | 2020-10-29 | Applied Materials Inc | Methods for depositing coatings on aerospace components |
WO2020219332A1 (fr) | 2019-04-26 | 2020-10-29 | Applied Materials, Inc. | Procédés de protection d'éléments aérospatiaux contre la corrosion et l'oxydation |
CN113236381A (zh) * | 2021-03-26 | 2021-08-10 | 北京航空航天大学 | 一种用于搭接层板接触面上的气膜孔进出口凹槽结构 |
Family Cites Families (54)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4743462A (en) * | 1986-07-14 | 1988-05-10 | United Technologies Corporation | Method for preventing closure of cooling holes in hollow, air cooled turbine engine components during application of a plasma spray coating |
US4937103A (en) * | 1988-05-12 | 1990-06-26 | Hess Suzanne M | Scratch a sketch |
JP2773050B2 (ja) | 1989-08-10 | 1998-07-09 | シーメンス アクチエンゲゼルシヤフト | 耐熱性耐食性の保護被覆層 |
DE3926479A1 (de) | 1989-08-10 | 1991-02-14 | Siemens Ag | Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit |
US5419971A (en) * | 1993-03-03 | 1995-05-30 | General Electric Company | Enhanced thermal barrier coating system |
KR100354411B1 (ko) | 1994-10-14 | 2002-11-18 | 지멘스 악티엔게젤샤프트 | 부식,산화및과도한열응력으로부터부품을보호하기위한보호층및그제조방법 |
US5558922A (en) * | 1994-12-28 | 1996-09-24 | General Electric Company | Thick thermal barrier coating having grooves for enhanced strain tolerance |
JPH09136260A (ja) * | 1995-11-15 | 1997-05-27 | Mitsubishi Heavy Ind Ltd | ガスタービン翼の冷却孔加工方法 |
US5609779A (en) * | 1996-05-15 | 1997-03-11 | General Electric Company | Laser drilling of non-circular apertures |
US6383602B1 (en) * | 1996-12-23 | 2002-05-07 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream which flows through a substrate, and related articles of manufacture |
EP0892090B1 (fr) | 1997-02-24 | 2008-04-23 | Sulzer Innotec Ag | Procédé de fabrication de structure monocristallines |
EP0861927A1 (fr) | 1997-02-24 | 1998-09-02 | Sulzer Innotec Ag | Procédé de fabrication de structures monocristallines |
JPH10299408A (ja) * | 1997-04-22 | 1998-11-10 | Hitachi Ltd | ガスタービン静翼 |
TW378246B (en) * | 1997-12-13 | 2000-01-01 | Lg Ind Systems Co Ltd | Ornamental steel plate and manufacturing method therefore |
WO1999067435A1 (fr) | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Alliage a solidification directionnelle a resistance transversale a la rupture amelioree |
US6074706A (en) * | 1998-12-15 | 2000-06-13 | General Electric Company | Adhesion of a ceramic layer deposited on an article by casting features in the article surface |
US6231692B1 (en) | 1999-01-28 | 2001-05-15 | Howmet Research Corporation | Nickel base superalloy with improved machinability and method of making thereof |
JP2003529677A (ja) | 1999-07-29 | 2003-10-07 | シーメンス アクチエンゲゼルシヤフト | 耐熱性の構造部材及びその製造方法 |
JP2001064761A (ja) * | 1999-08-24 | 2001-03-13 | Ishikawajima Harima Heavy Ind Co Ltd | 遮熱コーティング材の剥離防止構造および遮熱コーティング方法 |
US6234755B1 (en) * | 1999-10-04 | 2001-05-22 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture |
US6316078B1 (en) * | 2000-03-14 | 2001-11-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Segmented thermal barrier coating |
US6939603B2 (en) * | 2001-03-22 | 2005-09-06 | Siemens Westinghouse Power Corporation | Thermal barrier coating having subsurface inclusions for improved thermal shock resistance |
EP1275747B1 (fr) * | 2001-07-11 | 2011-02-23 | Alstom Technology Ltd | Procédé de revêtement d' un composant résistant à des températures élevées avec un revêtement de protection thermique et composant résistant à des températures élevées |
US6602053B2 (en) * | 2001-08-02 | 2003-08-05 | Siemens Westinghouse Power Corporation | Cooling structure and method of manufacturing the same |
US6703137B2 (en) * | 2001-08-02 | 2004-03-09 | Siemens Westinghouse Power Corporation | Segmented thermal barrier coating and method of manufacturing the same |
US8357454B2 (en) * | 2001-08-02 | 2013-01-22 | Siemens Energy, Inc. | Segmented thermal barrier coating |
US7204019B2 (en) * | 2001-08-23 | 2007-04-17 | United Technologies Corporation | Method for repairing an apertured gas turbine component |
DE50104022D1 (de) | 2001-10-24 | 2004-11-11 | Siemens Ag | Rhenium enthaltende Schutzschicht zum Schutz eines Bauteils gegen Korrosion und Oxidation bei hohen Temperaturen |
EP1319729B1 (fr) | 2001-12-13 | 2007-04-11 | Siemens Aktiengesellschaft | Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel |
US7411150B2 (en) * | 2002-06-12 | 2008-08-12 | Alstom Technology Ltd. | Method of producing a composite component |
DE60310168T2 (de) * | 2002-08-02 | 2007-09-13 | Alstom Technology Ltd. | Verfahren zum Schutz von Teilflächen eines Werkstücks |
US20040265488A1 (en) * | 2003-06-30 | 2004-12-30 | General Electric Company | Method for forming a flow director on a hot gas path component |
US7150926B2 (en) * | 2003-07-16 | 2006-12-19 | Honeywell International, Inc. | Thermal barrier coating with stabilized compliant microstructure |
FR2860741B1 (fr) * | 2003-10-10 | 2007-04-13 | Snecma Moteurs | Procede de reparation de pieces metalliques notamment d'aubes de turbine de moteur a turbine a gaz |
EP1712739A1 (fr) * | 2005-04-12 | 2006-10-18 | Siemens Aktiengesellschaft | Elément avec trou de refroidissement par film |
US7553534B2 (en) * | 2006-08-29 | 2009-06-30 | General Electric Company | Film cooled slotted wall and method of making the same |
US20080274336A1 (en) * | 2006-12-01 | 2008-11-06 | Siemens Power Generation, Inc. | High temperature insulation with enhanced abradability |
EP1942250A1 (fr) * | 2007-01-05 | 2008-07-09 | Siemens Aktiengesellschaft | Composant doté d'évidements s'étendant obliquement sur la surface et procédé de fonctionnement d'une turbine |
JP2008248733A (ja) * | 2007-03-29 | 2008-10-16 | Mitsubishi Heavy Ind Ltd | ガスタービン用高温部材 |
US20090246011A1 (en) * | 2008-03-25 | 2009-10-01 | General Electric Company | Film cooling of turbine components |
CN101715278B (zh) * | 2008-10-08 | 2012-07-04 | 深圳富泰宏精密工业有限公司 | 壳体及其制造方法 |
US8852720B2 (en) * | 2009-07-17 | 2014-10-07 | Rolls-Royce Corporation | Substrate features for mitigating stress |
CN102049957A (zh) * | 2009-10-29 | 2011-05-11 | 深圳富泰宏精密工业有限公司 | 陶瓷塑料复合制品及其制作方法 |
US8506243B2 (en) * | 2009-11-19 | 2013-08-13 | United Technologies Corporation | Segmented thermally insulating coating |
US8608443B2 (en) * | 2010-06-11 | 2013-12-17 | Siemens Energy, Inc. | Film cooled component wall in a turbine engine |
EP2586985A1 (fr) * | 2011-10-25 | 2013-05-01 | Siemens Aktiengesellschaft | Surface dotée d'un renfoncement formé de manière spécifique et composant |
EP2589682A1 (fr) * | 2011-11-07 | 2013-05-08 | Siemens Aktiengesellschaft | Couche d'isolation thermique en céramique sur une surface structurée et procédé de fabrication |
EP2597259A1 (fr) * | 2011-11-24 | 2013-05-29 | Siemens Aktiengesellschaft | Surface modifiée autour d'un trou |
CN103160772B (zh) * | 2011-12-16 | 2015-04-15 | 深圳富泰宏精密工业有限公司 | 陶瓷层的封孔方法及经由该方法制得的制品 |
US9416665B2 (en) * | 2012-02-15 | 2016-08-16 | United Technologies Corporation | Cooling hole with enhanced flow attachment |
US9709274B2 (en) * | 2013-03-15 | 2017-07-18 | Rolls-Royce Plc | Auxetic structure with stress-relief features |
WO2015077755A1 (fr) * | 2013-11-25 | 2015-05-28 | United Technologies Corporation | Structure à multiples parois refroidie par film ayant une ou plusieurs indentations |
US8939706B1 (en) * | 2014-02-25 | 2015-01-27 | Siemens Energy, Inc. | Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface |
US10024169B2 (en) * | 2015-02-27 | 2018-07-17 | General Electric Company | Engine component |
-
2012
- 2012-11-16 EP EP12192931.9A patent/EP2733310A1/fr not_active Withdrawn
-
2013
- 2013-11-05 EP EP13786472.4A patent/EP2904211A1/fr not_active Withdrawn
- 2013-11-05 WO PCT/EP2013/073001 patent/WO2014075947A1/fr active Application Filing
- 2013-11-05 US US14/442,152 patent/US20160281511A1/en not_active Abandoned
- 2013-11-05 CN CN201380059956.2A patent/CN104797783A/zh active Pending
- 2013-11-05 JP JP2015542212A patent/JP2015536406A/ja active Pending
- 2013-11-05 IN IN3152DEN2015 patent/IN2015DN03152A/en unknown
Also Published As
Publication number | Publication date |
---|---|
CN104797783A (zh) | 2015-07-22 |
WO2014075947A1 (fr) | 2014-05-22 |
IN2015DN03152A (fr) | 2015-10-02 |
JP2015536406A (ja) | 2015-12-21 |
EP2733310A1 (fr) | 2014-05-21 |
US20160281511A1 (en) | 2016-09-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2904211A1 (fr) | Surface modifiée autour d'un trou | |
EP2593582B1 (fr) | Système stratifié céramique poreux | |
EP2907888A1 (fr) | Aube de compresseur dotée d'un revêtement dur résistant à la corrosion | |
EP2436798A1 (fr) | Matériel de masquage, couche de masquage, procédé de masquage d'un substrat et procédé de revêtement d'un substrat | |
WO2012062546A1 (fr) | Système à couches poreux, muni d'une couche interne poreuse | |
EP2373824B1 (fr) | Procédé de revêtement d'un composant à trous de refroidissement par film et composant | |
EP2353725A1 (fr) | Buse de pulvérisation et procédé de pulvérisation atmosphérique, dispositif de revêtement et élément revêtu | |
EP2241397A1 (fr) | Soudage de trous, procédé de revêtement de tiges de soudage | |
WO2013053509A1 (fr) | Couche céramique double à base d'oxyde de zircon | |
EP2365106A1 (fr) | Système de couche d'isolation thermique en céramique doté d'une couche de raccordement modifiée | |
EP2584067A1 (fr) | Composant avec graphène et procédé de fabrication de composants avec graphène | |
WO2013075858A1 (fr) | Surface modifiée autour d'une ouverture | |
EP2733236A1 (fr) | Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur | |
EP2771546A1 (fr) | Surface pourvue de dépressions spécialement formées et élément | |
EP1806430A1 (fr) | Revêmtement céramique ayant une haute porositée, utilisation de celle-ci revêtement et composant comprenant telle revêtement | |
EP2082076A1 (fr) | Procédé d'optimisation de revêtement par un coupon et composant avec coupon | |
EP2247763A1 (fr) | Alliage, couche protectrice contre la corrosion à haute température et système stratifié | |
EP2592174A1 (fr) | Système de couche doté d'une surface de substrat structurée et son procédé de fabrication | |
EP2589681A1 (fr) | Combinaison de structures colonnaires et globulaires | |
WO2012065851A1 (fr) | Procédé raccourci pour le forage d'un trou | |
EP1932935A1 (fr) | Procédé de fabrication d'une aube de turbine avec une couche d'oxide, une aube de turbine et son utilisation, et procédé de fonctionnement d'une turbine | |
WO2011057661A1 (fr) | Composant comportant des zones de ductilité différente et procédé de fabrication d'un composant | |
EP2177643A1 (fr) | Procédé de réparation d'un superalliage à l'aide de la même poudre de superalliage et de céramique | |
EP2599890A1 (fr) | Couche en céramique protégée contre l'éclatement et système de couche | |
WO2010149189A1 (fr) | Barrettes de brasage, brasage de trous, procédé de revêtement |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20150324 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
DAX | Request for extension of the european patent (deleted) | ||
17Q | First examination report despatched |
Effective date: 20160615 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20161026 |