CONSTRUCTION ELEMENT HAVING A BOND STRUCTURE FOR A TURBO ENGINE, METHOD FOR THE PRODUCTION OF A CONSTRUCTION ELEMENT HAVING A BOND STRUCTURE FOR A TURBO ENGINE, AND TURBO ENGINE HAVING A CONSTRUCTION ELEMENT HAVING A BOND STRUCTURE

Abstract

A construction element, particularly adapted and configured for use in a turbo engine, in particular an aircraft engine, wherein a bond coat having a bond structure and thereabove a ceramic coat are disposed on a base. The lateral faces of the bond structure in the cross section are configured so as to be free of undercuts, wherein peak structures and/or trough structures are present, and the peak of the cross section of a peak structure has a mean peak angle () of less than or equal to 90, most particularly less than 45, and/or the trough structure has a valley angle in the range 90<170.

Claims

1. A construction element, particularly adapted and configured for use in a turbo engine, in particular an aircraft engine, wherein a bond coat having a bond structure and thereabove a ceramic coat are disposed on a base, wherein the lateral faces of the bond structure in the cross section are configured so as to be free of undercuts, wherein peak structures and/or trough structures are present, and the peak of the cross section of a peak structure has a mean peak angle () of less than or equal to 90, most particularly less than 45, and/or the trough structure has a valley angle () in the range 90<170.

2. The construction element according to claim 1, wherein the ratio of the thickness of the bond coat to the height of the bond structure is in the range from 0.1 to 10, particularly between 0.3 and 3.

3. The construction element according to claim 1, wherein the ratio of the height of the bond structures to the spacing of the bond structures is in the range from 0.1 to 5, particularly between 0.3 and 3.

4. The construction element according to claim 1, wherein the nominal roughness R.sub.a of the structured surface is 5 m to 25 m.

5. The construction element according to claim 1, wherein the bond structure is configured as a linear structure, as a punctiform structure, as a mesh structure, as a honeycomb structure, or as a corrugated structure from mutually parallel-running corrugations, or from superimpositions of said structures.

6. The construction element according to claim 5, wherein the maximum height of the cross section of the bond structure at crossover points of the bond structure, particularly in a mesh structure, can vary in relation to the height of the bond structure outside the crossover points.

7. The construction element according to claim 7, wherein the mean spacing between peaks of the bond structure is between 50 and 5000 m.

8. The construction element according to claim 1, wherein the bond structure has a substantially triangular cross section, particularly an isosceles triangular cross section.

9. The construction element according to claim 1, wherein the width of the cross section of the bond structure decreases uniformly from the surface of the bond coat to the peak.

10. The construction element according to claim 1, wherein the cross section of the bond structure is symmetrical to a perpendicular line through the peak or to the vertical central axis of a trough.

11. The construction element according to claim 1, wherein the ratio of the height of the cross section to the width at the base of the bond structure is between 0.1 and 10, particularly between 1 and 5.

12. The construction element according to claim 1, wherein the height of the cross section of the bond structure is between 50 and 500 m, particularly between 70 and 150 m.

13. The construction element according to claim 1, wherein the height of the cross section of the bond structure along the bond structure is substantially constant.

14. The construction element according to claim 1, wherein the bond structure is produced from a metallic and/or ceramic material, comprising a proportion of M CrAlY where M=Fe, Ni, and/or Co, M CrAl where M=Fe, Ni, and/or Co, NiAl, or NiAlPt yttrium-stabilized zirconium oxide (YSZ) aluminates pyrochlores and/or perovskite.

15. The construction element according to claim 1, wherein the ceramic coat comprises at least one oxidic ceramic, particularly containing magnesium spinel and/or aluminium oxide, particularly yttrium-stabilized zirconium oxide (YSZ), pyrochlores, or perovskites.

16. A method for the production of a construction element for a turbo engine according to claim 1, wherein a bond coat having a bond structure is applied to a base, and a ceramic coat is disposed thereabove, wherein the bond structure of the bond coat is generated by a laser ablation method.

17. The method according to claim 16, wherein the ceramic coat, particularly a YSZ coat and/or a magnesium spinel coat, is applied by an atmospheric plasma spray method.

18. The method according to claim 16, wherein a YSZ coat is applied to the bond coat by an atmospheric plasma spray method, and a magnesium spinel coat is applied thereabove by a suspension plasma spray method.

19. A turbo engine, particularly an aircraft engine, comprising at least one construction element according to claim 1, wherein the construction element is configured as part of a combustion chamber, as part of a wall of a turbine, and/or is configured in the intake region of a high-pressure part of a turbine.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The solution will be explained in conjunction with the embodiments illustrated in the figures.

[0038] FIG. 1 shows an illustration of a part of an aircraft engine having a construction element having a bond structure.

[0039] FIG. 2 shows a schematic sectional illustration through a first embodiment of a construction element having a bond structure having a peak structure.

[0040] FIG. 3 shows a schematic sectional illustration through a second embodiment of a construction element having a bond structure.

[0041] FIG. 4 shows a schematic sectional illustration through a third embodiment of a construction element having a bond structure having a trough structure.

[0042] FIG. 5 shows a perspective illustration of a further embodiment of a construction element having a mesh-type bond structure.

[0043] FIG. 6 shows a microscopic sectional view of the embodiment from FIG. 5, having a mesh-type bond structure.

[0044] FIG. 7 shows a microscopic sectional view of a further embodiment of a construction element.

[0045] FIG. 8A-F show schematic plan views of bond structures on a construction element.

DETAILED DESCRIPTION

[0046] An aircraft engine 20 as an exemplar of a turbo engine is illustrated in part in FIG. 1, temperature-resistant construction elements 10 (to be described hereunder) having a structured bond coat 2 (see FIG. 2 or 3, for example) being able to be used in said aircraft engine 20. The axially rear part of the aircraft engine 20 is illustrated here, that is to say that the compressor stages of the aircraft engine 20 are not illustrated.

[0047] Particularly high thermal loads are present in a combustion chamber 21. For this reason, plate-shaped construction elements 10 having a bond structure 4 (see FIG. 2 or 3, for example) can be disposed in the interior of the combustion chamber 21.

[0048] The highest temperature is present at the exit of the gases from the combustion chamber 21 and at the entry into a high-pressure stage 22 of the turbine. Additionally or alternatively construction elements 10 can therefore be disposed in the high-pressure stage 22. Said construction elements 10 herein are not configured as plates, but the coating is disposed directly in the region of the stator of the turbine, for example. The region of the stator per se thus becomes the coated construction element 10. In principle, it is also possible for the coated construction elements 10 to also have ducts or openings for cooling media.

[0049] It is furthermore also possible for blades of rotors and/or stators to be provided with the coating so that said blades become construction elements 10 in the context of the present description.

[0050] A further possibility lies in using the construction element 10 as a coating, that is to say as a so-called liner 23, in the wall of the turbine wall, that is to say particularly in those regions that are opposite the blades of the rotors. Liners 23 can be used in the regions in which rotor blades, for example of the turbine, are at least temporarily in mechanical contact with the wall of the casing. This is quite desirable at least for minimizing the gap between the wall and the turbine blade. The construction elements 10 having bond structures 4 and a ceramic coating 3 do not only have a high thermal load bearing capability, but in mechanical terms are also configured such that said construction elements 10 can be used as liners 23.

[0051] Liners 23 can also be used in combustion chambers, or the coating can become directly part of the combustion chamber wall.

[0052] In principle, the construction element 10 can be used at those locations where comparatively thick ceramic coats are usually disposed.

[0053] By way of the embodiments described here it is possible for a fine structuring to be applied directly to a bond coat material without compromising the metal base. Only minor thermal gradients within the construction elements 10 arise in operation. The adhesion of the bond coat on the base material 1 is also very positive. Said embodiments also have a high resistance to oxidation.

[0054] A sectional view through the surface of an embodiment of a construction element 10 is schematically illustrated in FIG. 2.

[0055] A bond coat 2 having bond structures 4 herein is disposed on a base 1. The structuring in the embodiment illustrated is composed of a three-dimensional mesh structure (see FIG. 4, for example) of which only the cross-sectional faces of three mesh elements (the bond structures 4) are illustrated in the sectional view of FIG. 2.

[0056] The bond structures 4 here are configured so as to be integral to the bond coat 2, since the bond coat 2 has been machined by an ablative laser method. This means that the bond structures 4 have been machined from the bond coat 2 such that said bond structures 4 extend vertically from the surface of the bond coat 2. This is referred to as a peak structure since the peaks 6 rise above a base area.

[0057] The cross-sectional faces of the bond structures 4 here are configured so as to be substantially triangular, wherein the two lateral faces 5 of the bond structure 4 here are configured so as to be of equal length; a symmetrical shape is present, wherein the axis of symmetry points from the peak 6 perpendicularly towards the base 1.

[0058] The angle at the peak 6 of the bond structure 4 here is approximately 40. The angle is measured from the peak 6, between the lateral faces 5.

[0059] The peak angle in alternative embodiments can be 90.

[0060] Furthermore, the lateral faces 5 are configured here so as to be straight, that is to say that there are particularly no undercuts.

[0061] A ceramic coat 3, for example from YSZ (yttrium-stabilized zirconium oxide) and/or magnesium spinel, is disposed above the bond coat 2.

[0062] The bond structure 4 having the inclined lateral faces 5 without undercuts offers a positive connection to the ceramic coat 3, wherein the peaks 6 of the bond structure 4 can ensure a targeted segmentation in the ceramic coat 3.

[0063] In the case of the targeted segmentation, cracks 7 are induced in the ceramic coat 3 so as to achieve a mechanical relaxation of tension. Said vertical cracks 7 can be configured in a particularly efficient manner when the bond structure 4 in an undercut-free manner tapers towards the top, that is to say towards the peak 6.

[0064] The height H of the bond structure 4, measured from the surface of the bond coat 2, is between 50 and 500 m; the height H in the embodiment illustrated is approx. 100 m. The ratio of the height H to the width B at the base of the bond structure 4 (that is to say on the surface of the bond coat 2) here is 1.25. Alternatively, the H-to-B ratio can be in the range between 1 and 10.

[0065] The embodiment according to FIG. 3 represents an alternative to this embodiment so that reference can be made to the relevant description of FIG. 2.

[0066] Here too, the width B of the cross section of the bond structure 4 decreases in a monotonous manner from the base on the surface to the bond coat 2 towards the peak 6. However, the lateral walls 5 here are in each case curved towards the inside. However, in both cases the cross sections of the bond structure 4 are symmetrical to the perpendicular line through the peak 6.

[0067] It is to be pointed out that the geometric ratios stated here cannot fully mirror the reality in terms of production technology, such as is illustrated by means of the following figures, for example. The numerical values in particular are thus to be understood as mean values, since there are always production-related deviations.

[0068] A further embodiment of an undercut-free bond structure is illustrated in FIG. 4, specifically a trough structure, that is to say that individual troughs 8 are incorporated in a base area of the bond coat 2. The troughs 8 have in each case a substantially square or rectangular floor area, wherein the flanks rise from the floor area towards the base area of the bond structure 2. The angle of the flanks in relation to the floor area is the valley angle of the trough 8. Said valley angle herein can be between 90 and 170. A valley angle of =90 would correspond to vertical walls. In the case of trough structures, the ratio of the height H of the cross section to the width B at the base of the bond structure 4 can also be less than one so that a range between 0.1 and 10 is possible in terms of the ratio.

[0069] A first embodiment for a mesh-type bond structure 4, in which a bond coat 2 from CoNiCrAlYafter being applied to the base not illustrated in FIG. 4is structured by an ablative laser method is illustrated in FIG. 5 (confocal laser microscope image). A ceramic coating 2 from YSZ and magnesium spinel is applied to the bond coat 2 by an atmospheric plasma spray method.

[0070] Some of the parameters of the laser ablation method for the production of the bond structure are listed below: [0071] laser output: in the kW range at peak output (the examples illustrated have been generated by a Trumph TruMark 5020 Laser (Nd:YAG) at a wavelength of 1062 nm); [0072] pulse length in the range of 100 nanoseconds; [0073] frequency of a few 100 kHz, in particular a few 10 kHz; [0074] beam diameter (a few 10 m); [0075] number of the sequential pulses in the range from 2 to 10; [0076] incorporating the bond structures by way of a meandering program.

[0077] The bond structures 4 here are configured as a mesh in which the mesh lines intersect one another in a substantially orthogonal manner. The lateral lengths of the mesh cells are substantially identical so that a square structural pattern is created. The maximum height Hmax of the cross section of the bond structure 4 at the crossover points of the mesh lines of the bond structure 4 is greater than the height H of the bond structure 4 outside the crossover points. The height H of the mesh structure 4 is substantially consistent between the crossover points.

[0078] The deviations from the idealized illustration of FIGS. 2 and 3 become evident in the high-resolution illustration of FIG. 5. However, it can be seen that the bond structure 4 in the cross section is without undercuts, and the peak angle is less than 90. This can likewise be clearly seen in the sectional image of FIG. 6 (SEM picture). The section plane here is perpendicular to the mesh lines. The peak angle of the bond structure 4 is plotted at one location.

[0079] A SEM sectional picture through another embodiment of a construction element 10 is illustrated in FIG. 7. Only the SPS-Mg-spinel coat is illustrated herein.

[0080] Here too, a bond coat 2 from CoNiCrAlY is machined by an ablative laser method in order to generate an undercut-free bond structure 4 which has a mean peak angle of less than 90.

[0081] A YSZ coat is applied to the bond coat 2 by an atmospheric plasma spray method. A magnesium-spinel coat which already has a specific degree of segmentation is then applied by a suspension plasma spray method (SPS). The ceramic coat 3 here thus comprises two layers from different materials.

[0082] The use of an ablative laser method for structuring is favourable in economic terms. It is also not necessary for complex peak structures to be shaped.

[0083] Different bond structures 4 are illustrated in FIGS. 8A to 8F. The bond structures 4 are particularly intended for preventing the ceramic high-temperature coating 3 from flaking in large areas. Also, cracks in the high-temperature coating 3 cannot extend in an arbitrary manner in the horizontal direction. The bond structures 4 here in can cross one another or be disposed so as to be mutually parallel.

[0084] A bond structure 4 which is formed from parallel linear elements is illustrated in FIG. 8A. The spacing L between the peaks 6 herein is between 500 and 5000 m. However, bond structures 4 do not mandatorily have to comprise only linear elements.

[0085] A corrugated bond structure 4 from curved elements that lie so as to be mutually parallel is illustrated in FIG. 8B. Here too, the spacing L between the elements is between 500 and 5000 m. A propagation of cracks can be particularly effectively suppressed in the case of an amplitude of the corrugated structure which is greater than the spacing L between the structural elements.

[0086] An embodiment in which the elements intersect one another is illustrated in FIG. 8C. A mesh structure as is illustrated in FIG. 5, for example, is created, wherein the spacing L between the parallel elements (that is to say between the peaks) is between 500 and 5000 m.

[0087] A honeycomb-shaped pattern which is constructed from linear elements is illustrated in FIG. 8D. The spacing L between two parallel elements is between 500 and 5000 m.

[0088] A punctiform pattern such as is present in a peak pattern, for example, is illustrated in FIG. 8E. The peak pattern here in can readily be configured so as to be regular, as is illustrated in FIG. 8E, or else random, as in FIG. 8F.

[0089] In principle, it is possible for a plurality of differently shaped undercut-free bond structures 4 and/or else patterns to be disposed on a construction element 10. The spacing L in a pattern can thus particularly be varied so as to ensure an optimal adaptation of the component 10 to thermal loads.

[0090] In principle, it is also possible for the patterns, for example the patterns illustrated in FIGS. 8A to 8E, to be combined with one another.

List of Reference Signs

[0091] 1 Base [0092] 2 Bond coat [0093] 3 Ceramic coat [0094] 4 Bond structure of the bond coat [0095] 5 Lateral faces of the bond structure [0096] 6 Peak of the cross section of a peak structure [0097] 7 Crack in the ceramic coat [0098] 8 Trough of a trough structure [0099] 10 Construction element [0100] 20 Aircraft engine (turbo engine) [0101] 21 Combustion chamber [0102] 22 High-pressure stage of a turbine [0103] 23 Liner [0104] Peak angle in the cross section of a peak structure of the bond structure [0105] Valley angle in the cross section of a trough structure of the bond structure [0106] B Width of the cross section of the bond structure [0107] H Height of the cross section of the bond structure [0108] Hmax Height of the cross section of the bond structure at crossover points [0109] L Spacing between peaks of a bond structure