CN102135018B - Coated turbine part and method for coating turbine part - Google Patents
Coated turbine part and method for coating turbine part Download PDFInfo
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- CN102135018B CN102135018B CN 201110056587 CN201110056587A CN102135018B CN 102135018 B CN102135018 B CN 102135018B CN 201110056587 CN201110056587 CN 201110056587 CN 201110056587 A CN201110056587 A CN 201110056587A CN 102135018 B CN102135018 B CN 102135018B
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Abstract
The invention relates a turbine part provided with different types of coatings at different parts. The coating is selected for being especially suitable for heat and corrosion conditions at the section of the part when in use. The invention also provides a method for coating the turbine part.
Description
The application is that application number is 200680054888.0 (PCT/EP 2006/005470), the applying date to be on June 8th, 2006, dividing an application with the patent application of inscribing
The method that the present invention relates to turbine part and apply turbine part.
Internal passages of gas turbine components is operated in and can damages in the height erosion environment condition of the parts in using.Said environmental nuisance maybe be in the hot combustion gas environment takes place with various forms, like particle erosion, dissimilar corrosion and the complex combination of oxidation and these infringement patterns.The speed of environmental nuisance can reduce through using protective layer.
For example well-known chromium can provide the outstanding protection to so-called I type and the heat erosion of II type.In this, the diffusion coating that generates through chromium and the diffusion of aluminium in alloy base material has been used to provide this protection for a long time.MCrAlY coating (wherein M is Ni or Co or both combinations) has been used as the alternate application of diffusion coating and has prevented oxidation in higher temperature.The chromium of known diffusion just can provide the outstanding protection to the II type heat erosion of lower temperature alone, and the ability strain.
The latest development is illustrated in and on the different piece of parts dissimilar coatings is provided is favourable.The selection of coating should make them be particularly suitable for heat and the etching condition that on the said part of said parts, occurs between the spreadable life.
US6,296,447Bl discloses a kind of internal passages of gas turbine components with barrier coating fixed with the position.Said parts are to have root, neck, platform and the turbine blade of the aerofoil profile of stretching out from said platform, and wherein said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing.First coating is provided at least a portion of said platform, and second coating is provided on the outer surface of aerofoil profile, and the 3rd coating is provided on the internal surface of aerofoil profile.The composition of first coating is different with second coating, and the composition of second coating is different with the 3rd coating.
But, still can observe various types of environmental nuisances, often make to expose (service exposure) replacement too early afterwards or repair parts in work.Therefore exist the needs of the improved guard method of internal passages of gas turbine components such as turbine blade and wheel blade particularly.
Therefore the object of the present invention is to provide the turbine part of heat-resisting and corrosion resistance and the method that applies turbine part is provided with raising.
First aspect of the present invention provides a kind of turbine part with root, neck, platform and aerofoil profile, and said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, and wherein on said root, provides first coating at least.
According to an embodiment, on said neck, can provide second coating.In this case, the composition of said first coating should be different with said second coating.
In addition, can also said second coating be provided on the outer surface of said aerofoil profile and at least a portion at said platform, and in addition the 3rd coating be provided on the internal surface of said aerofoil profile.Said in this case first, second has different compositions with the 3rd coating.
Said first coating can comprise and can ooze method (packcementation) or chemical vapor deposition (CVD) is diffused into the Cr in the parts through known method such as bag.
Experiment shows if said first coating layer that to be 5-25 μ m thick and/or contain the Cr of 15-30 weight % then can obtain the favorable protection performance.
Said second coating can comprise MCrAl Y, and wherein M can be Co or Ni or both combinations.Also can comprise further element such as Re, Si, Hf and/or Y in the said coating.A kind of preferred group of said coating becomes 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.
Can use different plasma spray technologies such as vacuum plasma spray coating (VPS), low pressure plasma spraying (LPPS), high-velocity oxy-fuel spraying (HVOF), cold air spraying (CGS) or plating.
Said second coating can further have one of following composition:
30 weight %Ni, 28 weight %Cr, 8 weight %Al, 0.6 weight %Y, 0.7 weight %Si, Co surplus;
28 weight %Ni, 24 weight %Cr, 10 weight %Al, 0.6 weight %Y and Co surplus;
23 weight %Cr, 10 weight %Co, 12 weight %Al, 0.6 weight %Y, 3.0 weight %Re, Ni surplus;
21 weight %Cr, 12 weight %Co, 11 weight %Al, 0.4 weight %Y and 2.0 weight %Re, the Ni surplus;
17 weight %Cr, 25 weight %Co, 10 weight %Al, 0.4 weight %Y and 1.5 weight %Re, the Ni surplus.
Said the 3rd coating can comprise Cr and Al.The Cr coating that preferably said coating is the Al modification, it can be diffused into Al in the chromising surface and provide through using known method such as CVD and ATP.According to find in the outer β layer the 3rd coating consist of 15-30 weight %Al and 5-15 weight %Cr demonstrates outstanding barrier propterty.
Perhaps, can on the internal surface of said aerofoil profile and the outer surface and at least a portion at said platform second coating be provided, and the 3rd coating can be provided on said neck.In this case, said first, second composition with the 3rd coating is different.
Said first coating that can comprise Cr can be oozed method or chemical vapor deposition (CVD) is diffused in the parts through known method such as bag.Experiment shows if said first coating layer that to be 5-25 μ m thick and/or contain 15-30 weight %Cr then can obtain the favorable protection performance.
According to an embodiment, said second coating can comprise Cr and Al.The Cr coating that preferably said coating is the Al modification, it can provide through using known method such as CVD and ATP that Al is diffused in the chromising surface.Certificate finds that the 3rd coating in the outer β layer consists of 15-30 weight %Al and 5-15 weight %Cr demonstrates outstanding barrier propterty.
Said the 3rd coating can comprise MCrAlY, and wherein M can be Co or Ni or both combinations.Also can comprise further element such as Re, Si, Hf and/or Y in the said coating.A kind of preferred group of said coating becomes 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.Can use different plasma spray technologies such as vacuum plasma spray coating (VPS), low pressure plasma spraying (LPPS), high-velocity oxy-fuel spraying (HVOF), cold air spraying (CGS) or plating.
Said the 3rd coating can further have one of following composition:
30 weight %Ni, 28 weight %Cr, 8 weight %Al, 0.6 weight %Y, 0.7 weight %Si, Co surplus;
28 weight %Ni, 24 weight %Cr, 10 weight %Al, 0.6 weight %Y and Co surplus;
23 weight %Cr, 10 weight %Co, 12 weight %Al, 0.6 weight %Y, 3.0 weight %Re, Ni surplus;
21 weight %Cr, 12 weight %Co, 11 weight %Al, 0.4 weight %Y and 2.0 weight %Re, the Ni surplus,
17 weight %Cr, 25 weight %Co, 10 weight %Al, 0.4 weight %Y and 1.5 weight %Re, the Ni surplus.
Preferably, the part to be coated of said platform is end face and/or side.
According to another embodiment of said first aspect, said first coating also can be provided on the said neck on the internal surface with said aerofoil profile.
On the outer surface of said aerofoil profile and on the end face of said platform and/or side second coating can be provided, the composition of said first and second coatings is different.
On said second coating on the outer surface of said aerofoil profile and on the end face of said platform and/or the side, the 3rd coating can also be provided.In this case, said first, second composition with the 3rd coating is different.
Said first coating that can comprise Cr can be oozed method or chemical vapor deposition (CVD) is diffused in the parts through known method such as bag.Experiment shows if said first coating layer that to be 5-25 μ m thick and/or contain 15-30 weight %Cr then can obtain the favorable protection performance.
Said second coating can comprise MCrAlY, and wherein M can be Co or Ni or both combinations.Also can comprise further element such as Re, Si, Hf and/or Y in the said coating.A kind of preferred group of said coating becomes 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.Can use different plasma spray technologies such as vacuum plasma spray coating (VPS), low pressure plasma spraying (LPPS), high-velocity oxy-fuel spraying (HVOF), cold air spraying (CGS) or plating.
Said second coating can further have one of following composition:
30 weight %Ni, 28 weight %Cr, 8 weight %Al, 0.6 weight %Y, 0.7 weight %Si, Co surplus;
28 weight %Ni, 24 weight %Cr, 10 weight %Al, 0.6 weight %Y and Co surplus;
23 weight %Cr, 10 weight %Co, 12 weight %Al, 0.6 weight %Y, 3.0 weight %Re, Ni surplus;
21 weight %Cr, 12 weight %Co, 11 weight %Al, 0.4 weight %Y and 2.0 weight %Re, Ni surplus;
17 weight %Cr, 25 weight %Co, 10 weight %Al, 0.4 weight %Y and 1.5 weight %Re, the Ni surplus.
The 3rd coating can comprise Al in addition.Preferably said coating uses known method such as CVD and ATP to cross aluminising.If the Al content of the outer surface of said second coating is 15-30 weight %, then can obtain the favorable protection performance.
Experiment shows if said coating does not comprise Pt then can obtain the favorable protection performance.
Said turbine part can by superalloy for example MarM247, IN6203 or CMSX4 constitute, and it can be provided by tradition or directional solidification casting technology.
According to a preferred embodiment, said turbine part is a turbine blade.
According to second aspect; Said purpose also is resolved through a kind of turbine part with root, neck, platform and aerofoil profile; Said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing; The internal surface of wherein said aerofoil profile has first coating, and the outer surface of said aerofoil profile has second coating, and said first and second coatings have different the composition.
According to an embodiment of said second aspect, said second coating is MCrAlY coating (M represents the combination of Ni, Co and/or Fe).
Said second coating can comprise 10-40 weight %Cr, 5-35 weight %Al, 0-2 weight %Y, 0-7 weight %Si, 0-2 weight %Hf, and surplus is mainly Ni and/or Co, and wherein all other element affixs account for gross weight less than 20 weight %.The composition of said second coating also can comprise 20-40 weight %Cr, 5-20 weight %Al, 0-1 weight %Y, 0-2 weight %Si, 0-1 weight %Hf, and surplus is mainly Ni and/or Co, and all other element affixs account for gross weight less than 20 weight %.Preferably said second coating comprises 25-40 weight %Cr, 5-15 weight %Al, 0-0.8 weight %Y, 0-0.5 weight %Si, 0-0.4 weight %Hf, and surplus is mainly Ni and/or Co, and all other element affixs account for gross weight less than 20 weight %.
According to a third aspect of the invention we, above-mentioned purpose also is achieved through a kind of turbine part with root, neck, platform and aerofoil profile, and said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, and wherein neck has first coating.
In addition; According to fourth aspect; Said purpose also is achieved through a kind of turbine part with root, neck, platform and aerofoil profile, and said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, and wherein said neck has first coating; And the bottom of said platform has second coating, and said first and second coatings have different the composition.
Further; According to a fifth aspect of the invention; Said purpose is achieved through a kind of turbine of first order blade and wheel blade and second level blade and wheel blade that comprises; Wherein said first order blade is according to any described turbine part among the claim 3-17, and said second level blade is according to any described turbine blade parts among the claim 18-32.
At last; According to a sixth aspect of the invention; This purpose is achieved through the method that a kind of coating has the turbine part of root, neck, platform and aerofoil profile, and wherein said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, and it may further comprise the steps.All outer surfaces and internal surface at said parts apply first coating.In the first portion of the said parts that scribble first coating, apply second coating then.At last on the second portion of the parts of said coating, apply the 3rd coating.Said first, second has different compositions with the 3rd coating.
In other words, the basic principle of this method is to apply whole said parts with first coating, is applying further coating on the part of the selection of said parts to improve heat resistance in the said appropriate section at said parts, corrosion resistance etc. then.Like this, can design turbine through the performance that provides different coating to have to satisfy the requirement in using.
Also can before applying said first coating, use unit and technological some part of covering said parts covered known in the art, particularly later will be coated with parts with the MCrAlY coating.In this case, the said concealed part of said parts will can be coated with said first coating.
According to an embodiment, said first coating is diffused in the said parts.This diffusion can be oozed method or chemical vapor deposition (CVD) realization through arbitrary suitable method such as bag.Particularly can Cr be diffused in the known compound that can provide the outstanding protection of heat erosion.Experiment shows if said first coating layer that to be 5-25 μ m thick and/or contain 15-30 weight %Cr then can obtain the favorable protection performance.
Preferably, the zone of said selection is the zone that in the use subsequently of said parts, can not bear high physical stress.This restriction has guaranteed that those zones of bearing higher physical stress of said parts only are coated with the chromium diffusion coating with anti-strain, and the anti-adaptability to changes of this coating can not be lowered because of applying further coating.
In the preferred embodiment aspect the said the 6th, said first portion comprises at least a portion of the outer surface and the said platform of said neck, said aerofoil profile, and the internal surface that said second portion is said aerofoil profile.
Said second coating can be coating, and it can comprise MCrAlY, and wherein M can be Co or Ni or both combinations.Also can comprise further element such as Re, Si, Hf and/or Y in the said coating.A kind of preferred group of said coating becomes 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.Can use different plasma spray technologies such as vacuum plasma spray coating (VPS), low pressure plasma spraying (LPPS), high-velocity oxy-fuel spraying (HVOF), cold air spraying (CGS) or plating.
Said second coating can also have one of following composition:
30 weight %Ni, 28 weight %Cr, 8 weight %Al, 0.6 weight %Y, 0.7 weight %Si, Co surplus;
28 weight %Ni, 24 weight %Cr, 10 weight %Al, 0.6 weight %Y and Co surplus;
23 weight %Cr, 10 weight %Co, 12 weight %Al, 0.6 weight %Y, 3.0 weight %Re, Ni surplus;
21 weight %Cr, 12 weight %Co, 11 weight %Al, 0.4 weight %Y and 2.0 weight %Re, the Ni surplus;
17 weight %Cr, 25 weight %Co, 10 weight %Al, 0.4 weight %Y and 1.5 weight %Re, the Ni surplus.
According to another embodiment, can be through diffusion, (above the pack ATP), applies the second and/or the 3rd coating, and they can comprise Al for example to pass through CVD or contactless coating method.
In the another preferred embodiment aspect the said the 6th, said first portion comprises at least a portion of internal surface and the outer surface and the said platform of said aerofoil profile, and said second portion comprises the said neck of said parts.
With the same in said first preferred embodiment, can said second coating be diffused in the said parts through CVD or ATP, wherein said second coating can comprise Al.
Said the 3rd coating can comprise MCrAlY, and wherein M can be Co or Ni or both combinations.Also can comprise further element such as Re, Si, Hf and/or Y in the said coating.A kind of preferred group of said coating becomes 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.Can use different plasma spray technologies such as vacuum plasma spray coating (VPS), low pressure plasma spraying (LPPS), high-velocity oxy-fuel spraying (HVOF), cold air spraying (CGS) or plating.
Said the 3rd coating also can have one of following composition:
30 weight %Ni, 28 weight %Cr, 8 weight %Al, 0.6 weight %Y, 0.7 weight %Si, Co surplus;
28 weight %Ni, 24 weight %Cr, 10 weight %Al, 0.6 weight %Y and Co surplus;
23 weight %Cr, 10 weight %Co, 12 weight %Al, 0.6 weight %Y, 3.0 weight %Re, Ni surplus;
21 weight %Cr, 12 weight %Co, 11 weight %Al, 0.4 weight %Y and 2.0 weight %Re, the Ni surplus,
17 weight %Cr, 25 weight %Co, 10 weight %Al, 0.4 weight %Y and 1.5 weight %Re, the Ni surplus.
Preferably, the part to be coated of said platform is end face and/or side.
Test shows if said coating does not comprise Pt, then can obtain the favorable protection result.
Method of the present invention can be used to apply can be by the superalloy turbine blade that constitutes of MarM247, IN6203 or CMSX4 for example.
Preferably, said turbine part is a turbine blade.
Below with reference to accompanying drawings the present invention is illustrated, wherein:
Fig. 1 is the perspective view according to the turbine blade of first embodiment of the invention,
Fig. 2 is the side view of turbine blade shown in Figure 1,
Fig. 3 is the longitudinal sectional view of turbine blade shown in Figure 2,
Fig. 4 is the cross sectional view of being done along the IV-IV line among Fig. 2,
Fig. 5 is the schematic representation of turbine blade shown in Figure 1,
Fig. 6 is the perspective view according to the turbine blade of second embodiment of the invention,
Fig. 7 is the side view of turbine blade shown in Figure 6,
Fig. 8 is the longitudinal sectional view of turbine blade shown in Figure 7,
Fig. 9 is the cross sectional view of being done along the IX-IX line among Fig. 7,
Figure 10 is the schematic representation of turbine blade shown in Figure 6,
Figure 11 is the perspective view according to the turbine blade of third embodiment of the invention,
Figure 12 is the side view of turbine blade shown in Figure 11,
Figure 13 is the longitudinal sectional view of turbine blade shown in Figure 12,
Figure 14 is the cross sectional view of being done along the XIV-XIV line among Figure 12,
Figure 15 is the schematic representation of turbine blade shown in Figure 11.
Fig. 1-5 has shown that according to turbine blade 1 of the present invention, it has root 2, neck 3, platform 4 and aerofoil profile 5, and wherein said aerofoil profile 5 has outer surface 6 and internal surface 7.
In this case, said turbine blade 1 is made up of superalloy MarM247, and provides through directional solidification casting technology.
Within aerofoil profile 5, internal surface 7 defines at least one cooling channel as shown in Figure 48.
On all outer surfaces of said blade 1 and internal surface, there is the first diffusion Cr coating.Its thick about 5-25 μ m, and comprise 15-30 weight %Cr.
Only at the qualifying part of said blade 1, promptly on the outer surface 6 and whole flat 4 of said neck 3, said aerofoil profile 5, the 2nd MCrAlY coating is provided on said first coating.
Said coating consist of 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.
Said the 2nd MCrAlY coating also can have following composition: 10-40 weight %Cr, 5-35 weight %Al, 0-2 weight %Y, 0-7 weight %Si, 0-2 weight %Hf and surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %; Preferably 20-40 weight %Cr, 5-20 weight %Al, 0-1 weight %Y, 0-2 weight %Si, 0-1 weight %Hf and surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %, more preferably 25-4 () weight %Cr, 5-15 weight %Al, 0-0.8 weight %Y, 0-0.5 weight %Si, 0-0.4 weight %Hf and surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %.
The part with said second coating of said blade 1 and the border that does not have between the said root 2 of said coating are represented by dot and dash line A.
The 3rd coating covers said first coating on the said internal surface 7.The Cr coating that said the 3rd coating is the Al modification, it consists of 15-30 weight %Al and 5-15 weight %Cr in β layer outside.
The distribution of said three kinds of different coating on said blade 1 is also shown among Fig. 5.Dotted line is represented first coating, dotted line (short drawing) expression second coating, and dotted line (dash) expression the 3rd coating.
For the turbine blade 1 of making said coating, all be coated with at all outer surfaces of the said blade 1 of first step and internal surface and be covered with Cr through the chemical vapor deposition diffusion.
Also can before applying said first coating, use unit and technological some part of covering said parts covered known in the art, particularly later will be coated with parts with the MCrAlY coating.In this case, the said concealed part of said parts will can be coated with said first coating.
In second step, MCrAlY is applied to said neck 3, said aerofoil profile 5 as second coating through high-velocity oxy-fuel spraying outer surface 6 and whole said platform 4 are to cover said first coating.Also can adopt other plasma spray technology.Importantly use the unit of covering that is fit to prevent accidental deposition (stray deposition) will be coated with on the part with second coating at said blade 1.
At last, apply the 3rd coating of the Cr coating form that is the Al modification.For this reason, Al is diffused in the internal surface 7 of chromising (first coating) of said aerofoil profile 5 through chemical vapor deposition.This has the outer β layer that expectation is formed with generation.
Fig. 6-10 has shown another according to turbine blade 1 of the present invention, and it has root 2, neck 3, platform 4 and aerofoil profile 5 equally, and wherein said aerofoil profile 5 has outer surface 6 and internal surface 7.In this case, said turbine blade 1 is made up of superalloy IN6203, and provides through traditional casting technique.
On all outer surfaces of said blade 1 and internal surface, there is the first diffusion Cr coating.Its thick about 5-25 μ m, and comprise 15-30 weight %Cr.
Zone selecting promptly on the outer surface and internal surface (6,7) and whole flat 4 of said aerofoil profile 5, provides second coating on said first coating.The Cr coating that said second coating is the Al modification, it has the outer β layer that consists of 15-30 weight %Al and 5-15 weight %Cr.The part with said second coating of said blade 1 and the border that does not have between the root 3 of said second coating are represented by dot and dash line B.
The 3rd coating that contains MCrAl Y covers said first coating between the online B and said root 2 on the said neck 3, and the border is represented with dot and dash line C.Said the 3rd coating has following composition: 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.
Said the 3rd MCrAlY coating also can have following composition: 10-40 weight %Cr, 5-35Al, 0-2 weight %Y, 0-7 weight %Si, 0-2Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %; Preferably 20-40 weight %Cr, 5-20Al, 0-1 weight %Y, 0-2 weight %Si, 0-1Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %; More preferably 25-40 weight %Cr, 5-15Al, 0-0.8 weight %Y, 0-0.5 weight %Si, 0-0.4Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %.
The distribution of said three kinds of different coating on said blade 1 is also shown among Figure 10.Dotted line is represented first coating, dotted line (dash) expression second coating, and dotted line (short drawing) expression the 3rd coating.
For the turbine blade 1 of making said coating, all oozed the method diffusion at all outer surfaces of the said blade 1 of first step and internal surface and be coated with and be covered with Cr through bag.
Also can before applying said first coating, use unit and technological some part of covering said parts covered known in the art, particularly later will be coated with parts with the MCrAlY coating.In this case, the said concealed part of said parts will can be coated with said first coating.
In second step, in the outer surface and internal surface 6,7 and whole said platform of the said aerofoil profile 5 through Al being diffused into chromising (first coating), preparation is second coating of the Cr coating form of Al modification.This has the outer β layer that expectation is formed with generation.
At last, apply MCrAlY through first coating of vacuum plasma spraying plating on said neck 3 as the 3rd coating.Importantly use the unit of covering that is fit to prevent that chance is deposited on will being coated with on the part with the 3rd coating of said blade 1.
Figure 11-15 has shown the 3rd according to turbine blade 1 of the present invention, and it has root 2, neck 3, platform 4 and aerofoil profile 5, and wherein said aerofoil profile 5 has outer surface 6 and internal surface 7.In this case, said turbine blade 1 is made up of superalloy CMSX4, and provides through directional solidification casting technology.Root 2 links to each other with neck 3, and neck 3 is supporting platform 4.Aerofoil profile 5 is stretched out from platform 4.Within aerofoil profile 5, internal surface 7 defines at least one cooling channel as shown in Figure 48.
The first diffusion Cr coating is provided on the internal surface 7 of said root 2, said neck 3 and said aerofoil profile 5.Its thick about 5-25 μ m, and comprise 15-30 weight %Cr.
Only at the qualifying part of said blade 1, promptly on the end face and side of the outer surface 6 of institute's aerofoil profile 5 and said platform 4, the 2nd MCrAlY coating is provided.Said coating consist of 30-70 weight %Ni, 30-50 weight %Co, 15-25 weight %Cr, 5-15 weight %Al and maximum 1 weight %Y.
Said the 2nd MCrAlY coating also can have one of following composition: 10-40 weight %Cr, 5-35Al, 0-2 weight %Y, 0-7 weight %Si, 0-2Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %; Preferably 20-40 weight %Cr, 5-20Al, 0-1 weight %Y, 0-2 weight %Si, 0-1Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %; More preferably 25-40 weight %Cr, 5-15Al, 0-0.8 weight %Y, 0-0.5 weight %Si, 0-0.4Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 weight %.
Border between the part with said second coating of said blade 1 and the part that does not have said coating of said platform 4 is represented by dot and dash line D.
The 3rd coating covers said second coating fully.It is provided on the outer surface 7 of said aerofoil profile 5 and on the end face and side of said platform 4.Said the 3rd coating comprises Al, and it was aluminising.Said second coating includes 15-30 weight %Al at its outer surface.
The distribution of said three kinds of different coating on said blade 1 is also shown among Figure 15.Dotted line is represented first coating, dotted line (short drawing) expression second coating, and dotted line (dash) expression the 3rd coating.
For the turbine blade 1 of making said coating, be coated with through the chemical vapor deposition diffusion at internal surface 7, neck 3 and the root 2 of the said aerofoil profile 5 of the said blade 1 of first step and be covered with Cr.Other part of blade 1 is protected in order to avoid be coated through the unit of covering that is fit to.
In second step, MCrAlY is used as second coating and is applied to through high-velocity oxy-fuel spraying on the end face and/or side of outer surface 6 and said platform 4 of said aerofoil profile 5.Also can adopt other plasma spray technology.Importantly use the unit of covering that is fit to prevent that chance is deposited on will being coated with on the part with second coating of said blade 1.
At last, on said second coating, apply the 3rd coating.For this reason, on the outer surface 6 of said aerofoil profile 5 and on the end face of said platform 4 and/or the side Al is being crossed aluminising through chemical vapor deposition.Producing aluminium content is the second surface outer surface of 15-30 weight %.
It should be noted that; In said two embodiments; Turbine blade 1 only has the said second and the 3rd coating in the zone of selecting, and the remaining part of blade 1 only scribbles the chromium diffusion coating of anti-strain, and the anti-adaptability to changes of this coating can not be lowered because of the said second and the 3rd applying of coating.
Claims (18)
1. turbine part (1); It has root (2), neck (3), platform (4) and aerofoil profile (5); Said aerofoil profile (5) has outer surface (6) and the internal surface (7) that defines the cooling channel of therefrom passing (8); Wherein providing first coating on the internal surface (7) of said aerofoil profile (5) and wherein providing second coating on the outer surface (6) in said aerofoil profile (5), said first and second coatings have different compositions; Wherein on said root (2), provide the 5th coating.
2. turbine part according to claim 1 (1), wherein said second coating is the MCrAlY coating, wherein M represents the combination of Ni and/or Co.
3. turbine part according to claim 2 (1); Wherein said second coating comprises 10-40 weight %Cr, 5-35 weight %Al, 0-2 weight %Y, 0-7 weight %Si, 0-2 weight %Hf; Surplus is mainly Ni and/or Co, and wherein all other element affixs account for gross weight less than 20 weight %.
4. turbine part according to claim 3 (1); Wherein said second coating comprises 20-40 weight %Cr, 5-20 weight %Al, 0-1 weight %Y, 0-2 weight %Si, 0-1 weight %Hf; Surplus is mainly Ni and/or Co, and wherein all other element affixs account for gross weight less than 20 weight %.
5. turbine part according to claim 4 (1); Wherein said second coating comprises 25-40 weight %Cr, 5-15 weight %Al, 0-0.8 weight %Y, 0-0.5 weight %Si, 0-0.4 weight %Hf; Surplus is mainly Ni and/or Co, and wherein all other element affixs account for gross weight less than 20 weight %.
6. according to any described turbine part (1) among the claim 1-5, wherein said second coating is diffusion aluminide or coating.
7. according to any described turbine part (1) among the claim 1-5, wherein said first coating is a diffusion aluminide.
8. according to any described turbine part (1) among the claim 1-5, wherein go up and/or on the downside of said platform (4), provide the 3rd coating at said platform (4).
9. turbine part according to claim 8 (1), wherein said the 3rd coating is different from said second coating.
10. turbine part according to claim 8 (1), wherein said the 3rd coating is different from said first coating.
11., wherein on said neck (3), provide the 4th coating according to any described turbine part (1) among the claim 1-5.
12. turbine part according to claim 11 (1), wherein said the 4th coating is different from said the 3rd coating.
13. turbine part according to claim 11 (1), wherein said the 4th coating is identical with said the 3rd coating.
14. turbine part according to claim 11 (1), wherein said the 4th coating is a coating.
15. turbine part according to claim 11 (1), wherein said the 4th coating is a coating, and it is the MCrAlY coating, or diffusion aluminide, or the chromising layer, or aluminized coating, or aluminising and chromising layer.
16. turbine part according to claim 1 (1), wherein said the 5th coating is different from said the 4th coating.
17. turbine part according to claim 1 (1), wherein said the 5th coating is identical with said the 4th coating.
18. according to claim 1,16 or 17 described turbine parts (1), wherein said layer 5 is aluminized coating, chromising layer or aluminising and aluminized coating.
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|---|---|---|---|
| CN 201110056587 CN102135018B (en) | 2006-06-08 | 2006-06-08 | Coated turbine part and method for coating turbine part |
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| CN 201110056587 CN102135018B (en) | 2006-06-08 | 2006-06-08 | Coated turbine part and method for coating turbine part |
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| CN2006800548880A Division CN101460708B (en) | 2006-06-08 | 2006-06-08 | Coated turbine component and method of coating a turbine component |
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| CN102135018A CN102135018A (en) | 2011-07-27 |
| CN102135018B true CN102135018B (en) | 2012-12-05 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6270318B1 (en) * | 1999-12-20 | 2001-08-07 | United Technologies Corporation | Article having corrosion resistant coating |
| US6296447B1 (en) * | 1999-08-11 | 2001-10-02 | General Electric Company | Gas turbine component having location-dependent protective coatings thereon |
| US6773817B1 (en) * | 1998-12-22 | 2004-08-10 | Mtu Aero Engines Gmbh | Antiabrasion coating |
| WO2005031038A1 (en) * | 2003-09-22 | 2005-04-07 | Mtu Aero Engines Gmbh | Wear-resistant layer, component comprising such a wear-resistant layer, and production method |
-
2006
- 2006-06-08 CN CN 201110056587 patent/CN102135018B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6773817B1 (en) * | 1998-12-22 | 2004-08-10 | Mtu Aero Engines Gmbh | Antiabrasion coating |
| US6296447B1 (en) * | 1999-08-11 | 2001-10-02 | General Electric Company | Gas turbine component having location-dependent protective coatings thereon |
| US6270318B1 (en) * | 1999-12-20 | 2001-08-07 | United Technologies Corporation | Article having corrosion resistant coating |
| WO2005031038A1 (en) * | 2003-09-22 | 2005-04-07 | Mtu Aero Engines Gmbh | Wear-resistant layer, component comprising such a wear-resistant layer, and production method |
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|---|---|
| CN102135018A (en) | 2011-07-27 |
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