Patent Application
20160251971
The following relates to a ceramic layer which has a two-ply structure, with different microstructures being present in the layers.
Ceramic layers are used, in particular, as thermal barrier layers in turbine blades and have a porosity.
Vertically segmented thermal barrier layers in which cracks are formed during coating by means of a subsequent treatment are likewise known.
However, there is the problem that when the porosity is increased to achieve greater thermal insulation, the erosion resistance of a thermal barrier layer, which is generally plasma-sprayed, is reduced.
The advantages are good thermal insulation and good erosion resistance.
Some of the embodiments will be described in detail, with reference to the following figures, wherein like designations denote like members, wherein:
The description and the figures represent only working examples of embodiments of the invention.
The metallic substrate 4 comprises, in particular, a cobalt- or nickel-based superalloy, in particular as shown in
A metallic bonding layer 7 has preferably been applied to the substrate 4 (
This metallic bonding layer 7 preferably comprises an alloy of the NiCoCrAl (X) type, on the surface of which a protective aluminum oxide layer (not shown) is formed during further coating or during operation (TGO).
A lower ceramic layer 10′ (
The porosity is preferably reported in percent by volume.
An APS process is preferably used for the lower ceramic layer 10′ as per
The lower ceramic layer 10′ preferably has a layer thickness of up to 1 mm.
The minimum thickness of the lower ceramic layer 10′ is at least 100 μm, very particularly preferably at least 150 μm (
The outermost, ceramic layer 13 in
The minimum layer thickness of the outermost ceramic layer 13 is 30 μm, in particular at least 50 μm (
The maximum layer thickness of the outermost ceramic layer 13 is not more than 500 μm, in particular not more than 300 μm (
The porosity of the segmented layers like that of the outermost ceramic layer 13 here corresponds to that from the known art.
In contrast to
The lower ceramic layer 10″ in
The minimum layer thickness of the outermost, ceramic layer 13 is 30 μm, in particular at least 50 μm.
The porosity of the lower ceramic layer 10″ in
The minimum layer thickness of the outermost, ceramic layer 13 is 30 μm, in particular at least 50 μm.
The lower ceramic layer 10′″ of the thermal barrier layer 15′″ has a porosity of preferably greater than 15% and has been produced by means of an APS process. However, the pores have been produced by spraying a ceramic powder, preferably by means of polymers.
This gives a characteristic microstructure of the pores.
The lower ceramic layer 10′″ can preferably have a layer thickness of a plurality of millimeters, in particular ≧2 mm.
The minimum layer thickness of the outermost, ceramic layer 13 is 30 μm, in particular at least 50 μm.
The lower ceramic layer 10IV of the two-ply, ceramic thermal barrier layer 15IV has been produced by the suspension plasma spraying (SPS) process and has a ductile columnar structure having a certain porosity of 4% and cracks up to <8%.
The outermost layer 13 in
Possible materials for the outermost, ceramic thermal barrier layers 15′, . . . 15IV are yttrium oxide, partially stabilized zirconium oxide or thermal barrier layers composed of fully stabilized zirconium oxide.
It is likewise possible to use pyrochlores such as gadolinium zirconate, gadolinium hafnate, lanthanum zirconate, gadolinium zirconate.
Here, the materials for the lower, ceramic layer 10′, 10″, . . . and the outermost layer 13 can be varied as a function of use conditions and production possibilities.
The two-ply outermost ceramic layer 15 is preferably the outermost layer of the layer system 1′, 1″, . . . .
The turbomachine can be a gas turbine of an aircraft or of a power station for generating electricity, a steam turbine or a compressor.
The blade 120, 130 has, in succession along the longitudinal axis 121, a fastening region 400, a blade platform 403 adjoining this and also a blade leaf 406 and a blade tip 415. As guide blade 130, the blade 130 can have a further platform (not shown) at its blade tip 415.
In the fastening region 400, there is a blade foot 183 which serves for fastening the rotor blades 120, 130 to a shaft or a disk (not shown).
The blade foot 183 is, for example, configured as a hammer head. Other configurations as Christmas tree foot or swallowtail foot are possible.
The blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the blade leaf 406.
In the case of conventional blades 120, 130, all regions 400, 403, 406 of the blade 120, 130 are, for example, made of massive metallic materials, in particular superalloys. Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
The blade 120, 130 can have been made by a casting process, including by means of directional solidification, by a forging process, by a milling process or combinations thereof.
Workpieces having a monocrystalline structure or structures are used as components for machines which are subjected to high mechanical, thermal and/or chemical stresses during operation.
The manufacture of such monocrystalline workpieces is carried out, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form a monocrystalline structure, i.e. the monocrystalline workpiece, or directionally.
Here, dendritic crystals are aligned along the heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and here referred to, in keeping with general language usage, as directionally solidified) or a monocrystalline structure, i.e. the entire workpiece consists of a single crystal. In these processes, the transition to globulitic (polycrystalline) solidification has to be avoided since transverse and longitudinal grain boundaries are necessarily formed by nondirectional growth and these nullify the good properties of the directionally solidified or monocrystalline component.
If general reference is made to directionally solidified microstructures, this encompasses both single crystals which have no grain boundaries or at most low-angle grain boundaries and also columnar crystal structures which do have grain boundaries running in the longitudinal direction but no transverse grain boundaries. These crystalline structures mentioned second are also referred to as directionally solidified microstructures.
Such processes are known from U.S. Pat. No. 6,024,792 and EP 0 892 090 A1.
The blades 120, 130 can likewise have coatings to protect against corrosion or oxidation, e.g. (MCrAlX; M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and/or silicon and/or at least one element of the rare earths, or hafnium (Hf)). Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
The density is preferably 95% of the theoretical density.
A protective aluminum oxide layer (TGO=thermally grown oxide layer) forms on the MCrAlX layer (as intermediate layer or as outermost layer).
The layer composition preferably comprises Co-30Ni-28Cr-8Al-0, 6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y. Apart from these cobalt-based protective coatings, preference is also given to using nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1.5Re.
A thermal barrier layer can be additionally present on the MCrAlX and is preferably the outermost layer and consists, for example, of ZrO2, Y2O3—ZrO2, i.e. it is unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide.
The thermal barrier layer covers the entire MCrAlX layer. Columnar grains are produced in the thermal barrier layer by suitable treatment processes, e.g. electron beam vaporization (EB-PVD).
Other coating processes are conceivable, e.g. atmospheric plasma spraying (APS), LPPS, VPS or CVD. The thermal barrier layer can have grains which are porous, have microcracks or have macrocracks for better thermal shock resistance. The thermal barrier layer is thus preferably more porous than the MCrAlX layer.
Refurbishment means that components 120, 130 have to be freed of any protective layers (e.g. by sand blasting) after they have been used. This is followed by removal of the corrosion and/or oxidation layers or products. Cracks in the component 120, 130 are optionally also repaired. This is followed by recoating of the component 120, 130 and renewed use of the component 120, 130.
The blade 120, 130 can be hollow or solid. When the blade 120, 130 is to be cooled, it is hollow and optionally has film cooling holes 418 (indicated by dashes).
Although the present invention has been disclosed in the form of preferred embodiments and variations thereon, it will be understood that numerous additional modifications and variations could be made thereto without departing from the scope of the invention.
For the sake of clarity, it is to be understood that the use of ‘a’ or ‘an’ throughout this application does not exclude a plurality, and ‘comprising’ does not exclude other steps or elements.
| Number | Date | Country | Kind |
|---|---|---|---|
| 13189688.8 | Oct 2013 | EP | regional |
This application claims priority to PCT Application No. PCT/EP2014/059738, having a filing date of May 13, 2014, based off of EP Application No. 13189688.8 having a filing date of Oct. 22, 2013, the entire contents of which are hereby incorporated by reference.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/EP2014/059738 | 5/13/2014 | WO | 00 |
