CN102174902B - Coated turbine component and method for coating turbine component - Google Patents
Coated turbine component and method for coating turbine component Download PDFInfo
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- CN102174902B CN102174902B CN 201110056575 CN201110056575A CN102174902B CN 102174902 B CN102174902 B CN 102174902B CN 201110056575 CN201110056575 CN 201110056575 CN 201110056575 A CN201110056575 A CN 201110056575A CN 102174902 B CN102174902 B CN 102174902B
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Abstract
The invention relates to a turbine component which is provided with different types of coatings at different parts of the turbine component. The coatings need to be selected to be especially suitable for heat and corrosion conditions appearing at the parts of the component in the using process. The invention also describes a method for coating the turbine component.
Description
The application is that application number is 200680054888.0 (PCT/EP2006/005470), 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.Described environmental nuisance may be in the hot combustion gas environment occurs with various forms, as particle erosion, dissimilar corrosion and the complex combination of oxidation and these infringement patterns.The speed of environmental nuisance can be by reducing with 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 to the diffusion in alloy base material by chromium and aluminium 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 alone the outstanding protection to the II type heat erosion of lower temperature, and the ability strain.
The latest development shows that it is favourable that dissimilar coating is provided on the different piece of parts.The selection of coating should make them be particularly suitable for heat and the etching condition that occurs between the spreadable life on the described part of described parts.
US6,296,447Bl disclose a kind of internal passages of gas turbine components with barrier coating fixed with the position.Described parts are to have root, neck, platform and the turbine blade of the aerofoil profile of stretching out from described platform, and wherein said aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing.The first coating is provided at least a portion of described platform, and the 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 the first coating is different from the second coating, and the composition of the second coating is different from the 3rd coating.
But, still can observe various types of environmental nuisances, often make in work expose (service exposure) replacement too early afterwards or repair parts.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 the heat-resisting and corrosion resistance with raising, and the method that applies turbine part is provided.
A first aspect of the present invention provides a kind of turbine part with root, neck, platform and aerofoil profile, and described aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, and wherein provides at least the first coating on described root.
According to an embodiment, can provide the second coating on described neck.In this case, the composition of described the first coating should be different from described the second coating.
In addition, can also provide described the second coating on the outer surface of described aerofoil profile and at least a portion at described platform, and provide the 3rd coating in addition on the internal surface of described aerofoil profile.Described first, second, and third coating has different compositions in this case.
Described the first coating can comprise can ooze method (packcementation) or chemical vapor deposition (CVD) by known method such as bag and be diffused into Cr in parts.
Experiment shows if described the first coating layer that to be 5-25 μ m thick and/or contain the Cr of 15-30 % by weight can obtain good barrier propterty.
Described the 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 described coating.A kind of preferred group of described coating becomes 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by 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 electroplate.
Described the second coating can further have one of following composition:
30 % by weight Ni, 28 % by weight Cr, 8 % by weight Al, 0.6 % by weight Y, 0.7 % by weight Si, Co surplus;
28 % by weight Ni, 24 % by weight Cr, 10 % by weight Al, 0.6 % by weight Y and Co surplus;
23 % by weight Cr, 10 % by weight Co, 12 % by weight Al, 0.6 % by weight Y, 3.0 % by weight Re, Ni surplus;
21 % by weight Cr, 12 % by weight Co, 11 % by weight Al, 0.4 % by weight Y and 2.0 % by weight Re, the Ni surplus;
17 % by weight Cr, 25 % by weight Co, 10 % by weight Al, 0.4 % by weight Y and 1.5 % by weight Re, the Ni surplus.
Described the 3rd coating can comprise Cr and Al.Preferably described coating is the Cr coating of Al modification, and it can be diffused into Al in the chromising surface and provide by using known method such as CVD and ATP.It is found that the 3rd coating in outer β layer consist of 15-30 % by weight Al and 5-15 % by weight Cr demonstrates outstanding barrier propterty.
Perhaps, can provide the second coating on the internal surface of described aerofoil profile and outer surface and at least a portion at described platform, and the 3rd coating can be provided on described neck.In this case, the composition of described first, second, and third coating is different.
Described first coating that can comprise Cr can be oozed method or chemical vapor deposition (CVD) is diffused in parts by known method such as bag.Experiment shows if described the first coating layer that to be 5-25 μ m thick and/or contain 15-30 % by weight Cr can obtain good barrier propterty.
According to an embodiment, described the second coating can comprise Cr and Al.Preferably described coating is the Cr coating of Al modification, and it can provide by with known method such as CVD and ATP, Al being diffused in the chromising surface.It is found that the 3rd coating in outer β layer consists of 15-30 % by weight Al and 5-15 % by weight Cr demonstrates outstanding barrier propterty.
Described 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 described coating.A kind of preferred group of described coating becomes 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by 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 electroplate.
Described the 3rd coating can further have one of following composition:
30 % by weight Ni, 28 % by weight Cr, 8 % by weight Al, 0.6 % by weight Y, 0.7 % by weight Si, Co surplus;
28 % by weight Ni, 24 % by weight Cr, 10 % by weight Al, 0.6 % by weight Y and Co surplus;
23 % by weight Cr, 10 % by weight Co, 12 % by weight Al, 0.6 % by weight Y, 3.0 % by weight Re, Ni surplus;
21 % by weight Cr, 12 % by weight Co, 11 % by weight Al, 0.4 % by weight Y and 2.0 % by weight Re, the Ni surplus,
17 % by weight Cr, 25 % by weight Co, 10 % by weight Al, 0.4 % by weight Y and 1.5 % by weight Re, the Ni surplus.
Preferably, the part to be coated of described platform is end face and/or side.
According to another embodiment of described first aspect, described the first coating also can be provided on described neck and the internal surface of described aerofoil profile on.
Can provide the second coating on the outer surface of described aerofoil profile and on the end face of described platform and/or side, the composition of described the first and second coatings is different.
Can also provide the 3rd coating on described the second coating on the outer surface of described aerofoil profile and on the end face of described platform and/or side.In this case, the composition of described first, second, and third coating is different.
Described first coating that can comprise Cr can be oozed method or chemical vapor deposition (CVD) is diffused in parts by known method such as bag.Experiment shows if described the first coating layer that to be 5-25 μ m thick and/or contain 15-30 % by weight Cr can obtain good barrier propterty.
Described the second coating can comprise MCrAlY, and wherein M can be Co or Ni or both combinations.Also can comprise further element such as R e, Si, Hf and/or Y in described coating.A kind of preferred group of described coating becomes 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by 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 electroplate.
Described the second coating can further have one of following composition:
30 % by weight Ni, 28 % by weight Cr, 8 % by weight Al, 0.6 % by weight Y, 0.7 % by weight Si, Co surplus;
28 % by weight Ni, 24 % by weight Cr, 10 % by weight Al, 0.6 % by weight Y and Co surplus;
23 % by weight Cr, 10 % by weight Co, 12 % by weight Al, 0.6 % by weight Y, 3.0 % by weight Re, Ni surplus;
21 % by weight Cr, 12 % by weight Co, 11 % by weight Al, 0.4 % by weight Y and 2.0 % by weight Re, Ni surplus;
17 % by weight Cr, 25 % by weight Co, 10 % by weight Al, 0.4 % by weight Y and 1.5 % by weight Re, the Ni surplus.
The 3rd coating can comprise Al in addition.Preferably described coating uses known method such as CVD and ATP to cross aluminising.If the Al content of the outer surface of described the second coating is the 15-30 % by weight, can obtain good barrier propterty.
Experiment shows if described coating does not comprise Pt can obtain good barrier propterty.
Described turbine part can by superalloy for example MarM247, IN6203 or CMSX4 consist of, and it can be provided by tradition or directional solidification casting technique.
According to a preferred embodiment, described turbine part is turbine blade.
According to second aspect, described purpose also is resolved by a kind of turbine part with root, neck, platform and aerofoil profile, described 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 the first coating, and the outer surface of described aerofoil profile has the second coating, and described the first and second coatings have different the composition.
According to an embodiment of described second aspect, described the second coating is MCrAlY coating (M represents the combination of Ni, Co and/or Fe).
Described the second coating can comprise 10-40 % by weight Cr, 5-35 % by weight Al, 0-2 % by weight Y, 0-7 % by weight Si, 0-2 % by weight Hf, and surplus is mainly Ni and/or Co, and wherein all other element affixs account for gross weight less than 20 % by weight.The composition of described the second coating also can comprise 20-40 % by weight Cr, 5-20 % by weight Al, 0-1 % by weight Y, 0-2 % by weight Si, 0-1 % by weight Hf, and surplus is mainly Ni and/or Co, and all other element affixs account for gross weight less than 20 % by weight.Preferably described the second coating comprises 25-40 % by weight Cr, 5-15 % by weight Al, 0-0.8 % by weight Y, 0-0.5 % by weight Si, 0-0.4 % by weight Hf, and surplus is mainly Ni and/or Co, and all other element affixs account for gross weight less than 20 % by weight.
According to a third aspect of the invention we, above-mentioned purpose also is achieved by a kind of turbine part with root, neck, platform and aerofoil profile, and described aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, and wherein neck has the first coating.
In addition, according to fourth aspect, described purpose also is achieved by a kind of turbine part with root, neck, platform and aerofoil profile, described aerofoil profile has outer surface and the internal surface that defines the cooling channel of therefrom passing, wherein said neck has the first coating, and the bottom of described platform has the second coating, and described the first and second coatings have different the composition.
Further, according to a fifth aspect of the invention, described purpose comprises that by a kind of the turbine of first order blade and wheel blade and second level blade and wheel blade is achieved, wherein said first order blade is the described turbine part of any one according to claim 3-17, and described second level blade is the described turbine blade parts of any one according to claim 18-32.
At last, according to a sixth aspect of the invention, this purpose is achieved by a kind of method that 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 comprises the following steps.All outer surfaces and internal surface at described parts apply the first coating.Then apply the second coating in the first portion of the described parts that scribble the first coating.At last apply the 3rd coating on the second portion of the parts of described coating.Described first, second, and third coating has different compositions.
In other words, the basic principle of this method is to apply whole described parts with the first coating, then applies further coating with the heat resistance in improving the described appropriate section at described parts, corrosion resistance etc. on the part of the selection of described parts.Like this, can design the turbine that the performance of the requirement in using can be provided by providing different coating to have.
Also can use some part that unit and technology are covered described parts of covering known in the art before applying described the first coating, particularly will be coated with later the parts of MCrAlY coating.In this case, the described concealed part of described parts will can not be coated with described the first coating.
According to an embodiment, described the first coating is diffused in described parts.This diffusion can be oozed method or chemical vapor deposition (CVD) realization by arbitrary suitable method such as bag.Particularly Cr can be diffused in the known compound that can provide the outstanding protection of heat erosion.Experiment shows if described the first coating layer that to be 5-25 μ m thick and/or contain 15-30 % by weight Cr can obtain good barrier propterty.
Preferably, the zone of described selection is can not bear the zone of high physical stress in the using subsequently of described parts.This restriction guaranteed described parts those bear the chromium diffusion coating that zone that higher building ought to power only is coated with anti-strain, and the anti-adaptability to changes of this coating can not be lowered because applying further coating.
In a preferred embodiment aspect the described the 6th, described first portion comprises at least a portion of outer surface and the described platform of described neck, described aerofoil profile, and the internal surface that described second portion is described aerofoil profile.
Described the 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 described coating.A kind of preferred group of described coating becomes 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by 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 electroplate.
Described the second coating can also have one of following composition:
30 % by weight Ni, 28 % by weight Cr, 8 % by weight Al, 0.6 % by weight Y, 0.7 % by weight Si, Co surplus;
28 % by weight Ni, 24 % by weight Cr, 10 % by weight Al, 0.6 % by weight Y and Co surplus;
23 % by weight Cr, 10 % by weight Co, 12 % by weight Al, 0.6 % by weight Y, 3.0 % by weight Re, Ni surplus;
21 % by weight Cr, 12 % by weight Co, 11 % by weight Al, 0.4 % by weight Y and 2.0 % by weight Re, the Ni surplus;
17 % by weight Cr, 25 % by weight Co, 10 % by weight Al, 0.4 % by weight Y and 1.5 % by weight Re, the Ni surplus.
According to another embodiment, can for example by CVD or contactless coating method (above the pack, ATP), apply the second and/or the 3rd coating by diffusion, they can comprise Al.
In another preferred embodiment aspect the described the 6th, described first portion comprises at least a portion of internal surface and outer surface and the described platform of described aerofoil profile, and described second portion comprises the described neck of described parts.
With the same in described first preferred embodiment, can described the second coating be diffused in described parts by CVD or ATP, wherein said the second coating can comprise Al.
Described 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 described coating.A kind of preferred group of described coating becomes 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by 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 electroplate.
Described the 3rd coating also can have one of following composition:
30 % by weight Ni, 28 % by weight Cr, 8 % by weight Al, 0.6 % by weight Y, 0.7 % by weight Si, Co surplus;
28 % by weight Ni, 24 % by weight Cr, 10 % by weight Al, 0.6 % by weight Y and Co surplus;
23 % by weight Cr, 10 % by weight Co, 12 % by weight Al, 0.6 % by weight Y, 3.0 % by weight Re, Ni surplus;
21 % by weight Cr, 12 % by weight Co, 11 % by weight Al, 0.4 % by weight Y and 2.0 % by weight Re, the Ni surplus,
17 % by weight Cr, 25 % by weight Co, 10 % by weight Al, 0.4 % by weight Y and 1.5 % by weight Re, the Ni surplus.
Preferably, the part to be coated of described platform is end face and/or side.
Test shows, if described coating does not comprise Pt, can obtain good Protection Results.
Method of the present invention can be used to apply can be by the superalloy turbine blade that consists of of MarM247, IN6203 or CMSX4 for example.
Preferably, described turbine part is 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 doing along the IV-IV line in Fig. 2,
Fig. 5 is the schematic diagram 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 doing along the IX-IX line in Fig. 7,
Figure 10 is the schematic diagram 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 doing along the XIV-XIV line in Figure 12,
Figure 15 is the schematic diagram of turbine blade shown in Figure 11.
Fig. 1-5 have 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, described turbine blade 1 is made of superalloy MarM247, and provides by directional solidification casting technique.
Within aerofoil profile 5, internal surface 7 defines at least one cooling channel 8 as shown in Figure 4.
There is the first diffusion Cr coating on all outer surfaces of described blade 1 and internal surface.Its thick approximately 5-25 μ m, and comprise 15-30 % by weight Cr.
Only at the qualifying part of described blade 1, namely on the outer surface 6 and whole platform 4 of described neck 3, described aerofoil profile 5, provide the 2nd MCrAlY coating on described the first coating.
Described coating consist of 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by weight Y.
described the 2nd MCrAlY coating also can have following composition: 10-40 % by weight Cr, 5-35 % by weight Al, 0-2 % by weight Y, 0-7 % by weight Si, 0-2 % by weight Hf and surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight, 20-40 % by weight Cr preferably, 5-20 % by weight Al, 0-1 % by weight Y, 0-2 % by weight Si, 0-1 % by weight Hf and surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight, 25-40 % by weight Cr more preferably, 5-15 % by weight Al, 0-0.8 % by weight Y, 0-0.5 % by weight Si, 0-0.4 % by weight Hf and surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight.
The part with described second coating of described blade 1 and the border that does not have between the described root 2 of described coating are represented by dot and dash line A.
The 3rd coating covers described the first coating on described internal surface 7.The Cr coating that described the 3rd coating is the Al modification, it consists of 15-30 % by weight Al and 5-15 % by weight Cr in β layer outside.
During the distribution of described three kinds of different coating on described blade 1 is also shown in Fig. 5.Dotted line represents the first coating, dotted line (short stroke) expression the second coating, and dotted line (dash) expression the 3rd coating.
For the turbine blade 1 of making described coating, all spread by chemical vapor deposition to be coated with at all outer surfaces of the described blade 1 of first step and internal surface and be covered with Cr.
Also can use some part that unit and technology are covered described parts of covering known in the art before applying described the first coating, particularly will be coated with later the parts of MCrAlY coating.In this case, the described concealed part of described parts will can not be coated with described the first coating.
At second step, MCrAlY is sprayed the outer surface 6 that is applied to described neck 3, described aerofoil profile 5 and whole described platform 4 to cover described the first coating as the second coating by high-velocity oxy-fuel.Also can adopt other plasma spray technology.Importantly prevent that with the unit of covering that is fit to accidental deposition (stray deposition) is on the part that will be coated with the second coating of described blade 1.
At last, apply the 3rd coating of the Cr coating form that is the Al modification.For this reason, Al is diffused into by chemical vapor deposition in the internal surface 7 of chromising (the first coating) of described aerofoil profile 5.This has with generation the outer β layer that expectation forms.
Fig. 6-10 have 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, described turbine blade 1 is made of superalloy IN6203, and provides by traditional casting technique.
There is the first diffusion Cr coating on all outer surfaces of described blade 1 and internal surface.Its thick approximately 5-25 μ m, and comprise 15-30 % by weight Cr.
Zone selecting namely on the outer surface and internal surface (6,7) and whole platform 4 of described aerofoil profile 5, provides the second coating on described the first coating.The Cr coating that described the second coating is the Al modification, it has the outer β layer that consists of 15-30 % by weight Al and 5-15 % by weight Cr.The part with described second coating of described blade 1 and the border that does not have between the root 3 of described the second coating are represented by dot and dash line B.
The 3rd coating that contains MCrAlY covers described the first coating between online B and described root 2 on described neck 3, and the border represents with dot and dash line C.Described the 3rd coating has following composition: 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by weight Y.
Described the 3rd MCrAlY coating also can have following composition: 10-40 % by weight Cr, 5-35Al, 0-2 % by weight Y, 0-7 % by weight Si, 0-2Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight; Preferably 20-40 % by weight Cr, 5-20Al, 0-1 % by weight Y, 0-2 % by weight Si, 0-1Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight; More preferably 25-40 % by weight Cr, 5-15Al, 0-0.8 % by weight Y, 0-0.5 % by weight Si, 0-0.4Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight.
During the distribution of described three kinds of different coating on described blade 1 is also shown in Figure 10.Dotted line represents the first coating, dotted line (dash) expression the second coating, and dotted line (short stroke) expression the 3rd coating.
For the turbine blade 1 of making described coating, all oozed the method diffusion by bag at all outer surfaces of the described blade 1 of first step and internal surface and be coated with and be covered with Cr.
Also can use some part that unit and technology are covered described parts of covering known in the art before applying described the first coating, particularly will be coated with later the parts of MCrAlY coating.In this case, the described concealed part of described parts will can not be coated with described the first coating.
At second step, in the outer surface and internal surface 6,7 and whole described platform of the described aerofoil profile 5 by Al being diffused into chromising (the first coating), preparation is the second coating of the Cr coating form of Al modification.This has with generation the outer β layer that expectation forms.
At last, apply MCrAlY as the 3rd coating by the vacuum plasma spraying plating to the first coating on described neck 3.Importantly prevent from accidentally being deposited on the part that will be coated with the 3rd coating of described blade 1 with the unit of covering that is fit to.
Figure 11-15 have 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, described turbine blade 1 is made of superalloy CMSX4, and provides by directional solidification casting technique.Root 2 is connected 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 8 as shown in Figure 4.
The first diffusion Cr coating is provided on the internal surface 7 of described root 2, described neck 3 and described aerofoil profile 5.Its thick approximately 5-25 μ m, and comprise 15-30 % by weight Cr.
Only at the qualifying part of described blade 1, namely on the end face and side of the outer surface 6 of institute's aerofoil profile 5 and described platform 4, provide the 2nd MCrAlY coating.Described coating consist of 30-70 % by weight Ni, 30-50 % by weight Co, 15-25 % by weight Cr, 5-15 % by weight Al and maximum 1 % by weight Y.
Described the 2nd MCrAlY coating also can have one of following composition: 10-40 % by weight Cr, 5-35Al, 0-2 % by weight Y, 0-7 % by weight Si, 0-2Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight; Preferably 20-40 % by weight Cr, 5-20Al, 0-1 % by weight Y, 0-2 % by weight Si, 0-1Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight; More preferably 25-40 % by weight Cr, 5-15Al, 0-0.8 % by weight Y, 0-0.5 % by weight Si, 0-0.4Hf, surplus be mainly Ni and/or Co and all other element affixs account for gross weight less than 20 % by weight.
Border between the part with described second coating of described blade 1 and the part that does not have described coating of described platform 4 is represented by dot and dash line D.
The 3rd coating covers described the second coating fully.It is provided on the outer surface 7 of described aerofoil profile 5 and on the end face and side of described platform 4.Described the 3rd coating comprises Al, and it was aluminising.Described the second coating includes 15-30 % by weight Al at its outer surface.
During the distribution of described three kinds of different coating on described blade 1 is also shown in Figure 15.Dotted line represents the first coating, dotted line (short stroke) expression the second coating, and dotted line (dash) expression the 3rd coating.
For the turbine blade 1 of making described coating, spread by chemical vapor deposition to be coated with at internal surface 7, neck 3 and the root 2 of the described aerofoil profile 5 of the described blade 1 of first step and be covered with Cr.Protected in order to avoid coated by the unit by suitable covering for the other parts of blade 1.
At second step, MCrAlY is used as the second coating and sprays on the end face and/or side of the outer surface 6 that is applied to described aerofoil profile 5 and described platform 4 by high-velocity oxy-fuel.Also can adopt other plasma spray technology.Importantly prevent from accidentally being deposited on the part that will be coated with the second coating of described blade 1 with the unit of covering that is fit to.
At last, apply the 3rd coating on described the second coating.For this reason, on the outer surface 6 of described aerofoil profile 5 and on the end face of described platform 4 and/or side, Al is being crossed aluminising by chemical vapor deposition.Producing aluminium content is the second surface outer surface of 15-30 % by weight.
It should be noted that, in described two embodiments, turbine blade 1 only has the described 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 described second and the 3rd applying of coating.
Claims (12)
1. turbine part (1), it has root (2), neck (3), platform (4) and aerofoil profile (5), described aerofoil profile (5) has outer surface (6) and the internal surface (7) that defines the cooling channel (8) of therefrom passing, and wherein provides the first coating at least on described neck (3); Wherein said the first coating is coating, and it is selected from the MCrAlY layer, aluminising MCrAlY layer, aluminide or aluminide and MCrAlY layer.
2. turbine part (1), it has root (2), neck (3), platform (4) and aerofoil profile (5), described aerofoil profile (5) has outer surface (6) and the internal surface (7) that defines the cooling channel (8) of therefrom passing, wherein provide the first coating on described neck (3), provide the second coating on the bottom of described platform (4), described the first and second coatings have different compositions; Wherein said the first coating is coating, and it is selected from the MCrAlY layer, aluminising MCrAlY layer, aluminide or aluminide and MCrAlY layer.
3. turbine part according to claim 1 (1), wherein the downside at described platform (4) provides described the first coating.
4. the described turbine part of any one (1) according to claim 1-2, wherein provide the 3rd coating that is different from described the first coating on described aerofoil profile (5).
5. the turbine part (1) described according to claim 4, the wherein said second or the 3rd coating is coating.
6. the turbine part (1) described according to claim 5, the wherein said second or the 3rd coating is the MCrAlY layer, aluminising MCrAlY layer, aluminide or aluminide and MCrAlY layer.
7. the described turbine part of any one (1) according to claim 1-2, wherein provide the 4th coating on described internal surface (7).
8. the turbine part (1) described according to claim 7, wherein said the 4th coating is diffusion aluminide, Chromizing Layer or aluminising Chromizing Layer.
9. the turbine part (1) described according to claim 7, wherein provide the 5th coating on described root (2).
10. the turbine part (1) described according to claim 8, wherein provide the 5th coating on described root (2).
11. the turbine part according to claim 9 (1), wherein said the 5th coating are diffusion aluminide, aluminized coating, Chromizing Layer or aluminising Chromizing Layer.
12. turbine part according to claim 9 (1), wherein said the 5th coating is different from described the 4th coating.
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| CN102174902B true CN102174902B (en) | 2013-11-06 |
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Effective date of registration: 20220408 Address after: Munich, Germany Patentee after: Siemens energy global Corp. Address before: Munich, Germany Patentee before: SIEMENS AG |