WO2016087143A1 - Long, continuous engraving along a row of cooling holes - Google Patents

Long, continuous engraving along a row of cooling holes Download PDF

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Publication number
WO2016087143A1
WO2016087143A1 PCT/EP2015/075390 EP2015075390W WO2016087143A1 WO 2016087143 A1 WO2016087143 A1 WO 2016087143A1 EP 2015075390 W EP2015075390 W EP 2015075390W WO 2016087143 A1 WO2016087143 A1 WO 2016087143A1
Authority
WO
WIPO (PCT)
Prior art keywords
engraving
row
component according
substrate
cooling holes
Prior art date
Application number
PCT/EP2015/075390
Other languages
French (fr)
Inventor
Fathi Ahmad
Christian Menke
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to CN201580065045.XA priority Critical patent/CN107002250A/en
Priority to EP15790513.4A priority patent/EP3198057A1/en
Priority to JP2017529371A priority patent/JP6445160B2/en
Priority to US15/528,866 priority patent/US20170314399A1/en
Publication of WO2016087143A1 publication Critical patent/WO2016087143A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • 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
    • 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
    • C23C28/34—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
    • 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
    • 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
    • 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
    • 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
    • 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
    • F05D2230/10—Manufacture by removing 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
    • 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
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • This invention relates to a ceramic surface structure, wherein a long engraving is present along a row of cooling holes.
  • the highly loaded turbine blades and vanes require the application of different protection technologies in order to be able to withstand the high thermal loading.
  • the front stages of the turbine blades and vanes require a ceramic coating and the film cooling technology as well as the internal cooling.
  • the manufacturing of the film cooling holes could be one of the reasons for the ceramic coating spallation.
  • Parameters of the laser drilling causes cracks within the ceramic coating, which later spalls down and restricts the operation of the component.
  • Figures 1, 3, 4 show a view on top of the surface of a
  • Figure 2 shows a cross-section area of Figure 1.
  • This manufacturing procedure has following advantage: ⁇ The engraving will not reduce the bond coat thickness as during a laser engraving
  • the width of such a ceramic free region could vary between 1 and 2mm.
  • the positive effect of the engraving is the spallation behavior. In case of spallation the spalled region will not be extended on wide regions.
  • Another positive effect of the engraving is the vortices introduced due to the no-APS regions, which forces the hot gas flow to stick to the wall as by the dimples on a golf ball.
  • the step within the ceramic coating will be smoothened as well as the APS smoothening procedure will help breaking the edges.
  • Figure 1 shows a view on the top of a ceramic coating 25 ( Figure 2) .
  • the thermal barrier coating 25 (TBC) is part of a component 1 which has a substrate 22 ( Figure 2) wherein on top of the substrate 22 the thermal barrier coating 25 is applied.
  • This component 1 has at least one row 7 of cooling holes 10', 10'',..., which are during use of the component 1 overflowed by hot gas according the arrow 13, especially almost
  • the direction 14 is straight or has only one or two times a break of slope of maximum 25°.
  • These engravings 16, 19 are continuous, especially straight engravings in the TBC 25.
  • the engravings 16, 19, 20, 116, 216, 31 (Fig. 3, 4) are not endless, e. g. not a circle or not a square or not closed looped.
  • the engravings 16, 19, 20, 116, 216, 31 start especially at the beginning and end at the end of a row 7.
  • the engravings can also arranged only in the TBC 25.
  • the engravings 16, 19 have a depth until the substrate 22. But nevertheless the surface of the substrate 22 can
  • a metallic bond coat like a NiCoCrAl plus optional additives (Y, Re, Si, Ta, ...) .
  • Figures 3, 4 show a curved form of the engravings 20, 116, 216, 31, wherein the distance of opposite curved engraving 116, 20; 216, 31 is smaller between two cooling holes 10', 10'' and which are not straight (Fig. 4), but multiple curved or a combination of it (Fig. 3) .

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Abstract

By continuously long engravings the spallation behavior of the thermal barrier coating is reduced and the lifetime of the TBC is prolonged.

Description

Long, continuous engraving along a row of cooling holes
This invention relates to a ceramic surface structure, wherein a long engraving is present along a row of cooling holes.
The highly loaded turbine blades and vanes require the application of different protection technologies in order to be able to withstand the high thermal loading. The front stages of the turbine blades and vanes require a ceramic coating and the film cooling technology as well as the internal cooling.
The application of such technologies is helpful as long as the combination works during operation and no spallation occurs or nor cooling holes blockage is noticed.
The manufacturing of the film cooling holes could be one of the reasons for the ceramic coating spallation.
Parameters of the laser drilling causes cracks within the ceramic coating, which later spalls down and restricts the operation of the component.
On the other hand it is not possible to reduce the laser drilling energy to a very low level due to the fact that no drilling will take place with low energy.
It is therefore the aim of the invention to improve the lifetime of a ceramic coating and preventing the overall spallation of a TBC . This problem is solved by a ceramic surface structure according to claim 1.
In the dependent claims further developments are disclosed which can be arbitrarily combined which each other to yield further new advantages.
Figures 1, 3, 4 show a view on top of the surface of a
TBC and a row of cooling holes, Figure 2 shows a cross-section area of Figure 1.
By an implementation of a polymer masking it is possible to introduce the suggested design in figures 1 - 4. The polymer masking will provide a ceramic free region along the cooling holes .
This manufacturing procedure has following advantage: · The engraving will not reduce the bond coat thickness as during a laser engraving
• This step can be carried out during the coating
• In case of casting and coating deviations, the polymer masking will not affect the bond coat thickness.
The width of such a ceramic free region could vary between 1 and 2mm.
The positive effect of the engraving is the spallation behavior. In case of spallation the spalled region will not be extended on wide regions.
Another positive effect of the engraving is the vortices introduced due to the no-APS regions, which forces the hot gas flow to stick to the wall as by the dimples on a golf ball. During operation the step within the ceramic coating will be smoothened as well as the APS smoothening procedure will help breaking the edges.
The following positive effects are related to the engraving:
• Retrofitable with current designs
• In case of spallation, only restricted region will be affected
• Lower operation risk
· Reduced rework after laser drilling
• Applicable to all spallation threatened cooling holes rows
• Applicable to vanes and blades. Figure 1 shows a view on the top of a ceramic coating 25 (Figure 2) .
The thermal barrier coating 25 (TBC) is part of a component 1 which has a substrate 22 (Figure 2) wherein on top of the substrate 22 the thermal barrier coating 25 is applied.
This component 1 has at least one row 7 of cooling holes 10', 10'',..., which are during use of the component 1 overflowed by hot gas according the arrow 13, especially almost
perpendicular to the direction 14 of the row 7. The direction 14 is straight or has only one or two times a break of slope of maximum 25°.
Along the direction 14 of the row 7 of the cooling holes 10', 10'', ... there is especially only before the row 7 an
engraving 16 and/or after the row 7 a second engraving 19.
These engravings 16, 19 are continuous, especially straight engravings in the TBC 25.
The engravings 16, 19, 20, 116, 216, 31 (Fig. 3, 4) are not endless, e. g. not a circle or not a square or not closed looped. The engravings 16, 19, 20, 116, 216, 31 start especially at the beginning and end at the end of a row 7.
The distance between two engravings 16, 19, 20, 116, 216, 31 before and after the one row 7 next to each other is
especially 1mm to 2mm.
Furthermore the engravings can also arranged only in the TBC 25. In Figure 2 it can be seen that the engravings 16, 19 have a depth until the substrate 22. But nevertheless the surface of the substrate 22 can
coated with a metallic bond coat like a NiCoCrAl plus optional additives (Y, Re, Si, Ta, ...) .
Figures 3, 4 show a curved form of the engravings 20, 116, 216, 31, wherein the distance of opposite curved engraving 116, 20; 216, 31 is smaller between two cooling holes 10', 10'' and which are not straight (Fig. 4), but multiple curved or a combination of it (Fig. 3) .

Claims

Patent claims
1. Component ( 1 ) ,
which comprises:
a substrate (22)
a ceramic thermal barrier coating (25) on the substrate (22) ,
at least one row (7) of cooling holes (10', 10'', ...) along a direction (14) in the substrate (4) and in the thermal barrier coating (25) ,
wherein the thermal barrier coating (25) has at least one engraving,
characterized by that,
that the at least one engraving is a long continuous engraving (16, 19, 116, 20, 216, 31) along the direction
(14) before and/or after of the at least one row (7) .
2. Component according to claim 1,
wherein the engraving (16, 19, 20) is straight.
3. Component according to one or both of the claims 1 or 2, wherein the engraving (116, 216, 31) is multiple curved.
4. Component according to one or any of the preceding claims ,
wherein the engraving (16, 19, 20, 116, 216, 31) is long and continuous and which is not connecting with each other or endless.
5. Component according to one or any of the preceding claims,
wherein several engravings (16, 19, 20, 116, 216, 31) are arranged in the thermal barrier coating (25) .
6. Component according to one or any of the claims 1, 2, 3 4 or 5,
wherein the engraving (16, 19, 116, 20, 216, 31) is only arranged before and after one row (7) .
7. Component according to one or any of the claims 1, 2, 3, 4, 5 or 6,
wherein the substrate (22) has a metallic overlay coating.
8. Component according claim 7,
wherein the engraving (16, 19, 20, 116, 216, 31) has a depth that reaches the outer surface of a metallic coating on the substrate (4) .
9. Component according to one or any of the preceding claims ,
wherein the engraving (16, 19, 20, 116, 216, 31) is only arranged in the thermal barrier coating and does not reach the substrate (4) or a metallic coating.
10. Component to one or any of the preceding claims,
wherein the engraving (16, 19, 116, 216, 31) starts at the beginning and ends at the end of a row (7) .
11. Component to one or any of the preceding claims,
wherein both engravings (16, 19, 116, 216, 31) have a distance to each other along an overflow direction (13) of 1mm to 2mm.
12. Component to one or any of the preceding claims 3 to 11, wherein the distance of a curved engraving (116, 20; 216, 31) to a straight engraving (20) or to a curved engraving (31) is smaller between two cooling holes (10", 10"") of these two engravings.
13. Component according to one or any of the preceding
cl aims ,
wherein the substrate (22) is a nickel- or cobalt-based super alloy.
PCT/EP2015/075390 2014-12-02 2015-11-02 Long, continuous engraving along a row of cooling holes WO2016087143A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
CN201580065045.XA CN107002250A (en) 2014-12-02 2015-11-02 Along the continuous engraving portion of the length of the row of Cooling Holes
EP15790513.4A EP3198057A1 (en) 2014-12-02 2015-11-02 Long, continuous engraving along a row of cooling holes
JP2017529371A JP6445160B2 (en) 2014-12-02 2015-11-02 Long continuous engraving along a row of cooling holes
US15/528,866 US20170314399A1 (en) 2014-12-02 2015-11-02 Long, continuous engraving along a row of cooling holes

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14195844.7A EP3029176A1 (en) 2014-12-02 2014-12-02 Long, continuous engraving along a row of cooling holes
EP14195844.7 2014-12-02

Publications (1)

Publication Number Publication Date
WO2016087143A1 true WO2016087143A1 (en) 2016-06-09

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PCT/EP2015/075390 WO2016087143A1 (en) 2014-12-02 2015-11-02 Long, continuous engraving along a row of cooling holes

Country Status (5)

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US (1) US20170314399A1 (en)
EP (2) EP3029176A1 (en)
JP (1) JP6445160B2 (en)
CN (1) CN107002250A (en)
WO (1) WO2016087143A1 (en)

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Publication number Priority date Publication date Assignee Title
US11585224B2 (en) 2020-08-07 2023-02-21 General Electric Company Gas turbine engines and methods associated therewith

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EP1245787A2 (en) * 2001-03-27 2002-10-02 General Electric Company Cooling a coated turbine blade tip
US20090017260A1 (en) * 2001-08-02 2009-01-15 Kulkarni Anand A Segmented thermal barrier coating
US8317473B1 (en) * 2009-09-23 2012-11-27 Florida Turbine Technologies, Inc. Turbine blade with leading edge edge cooling
US20140174092A1 (en) * 2012-12-20 2014-06-26 United Technologies Corporation Closure of Cooling Holes with a Filling Agent

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US5073433B1 (en) * 1989-10-20 1995-10-31 Praxair Technology Inc Thermal barrier coating for substrates and process for producing it
EP2100984A1 (en) * 2008-03-14 2009-09-16 Siemens Aktiengesellschaft Method for masking cooling holes and device for using in a masking process for masking cooling holes
US8852720B2 (en) * 2009-07-17 2014-10-07 Rolls-Royce Corporation Substrate features for mitigating stress
US8608443B2 (en) * 2010-06-11 2013-12-17 Siemens Energy, Inc. Film cooled component wall in a turbine engine

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EP3198057A1 (en) 2017-08-02
US20170314399A1 (en) 2017-11-02

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