FUSED SAND-RESISTANT TURBINE PART

Abstract

The present invention relates to a turbine part, comprising a substrate, an environmental barrier comprising at least one layer selected from a thermally insulating layer, a sub-layer adapted to promote adhesion between the substrate and a thermally insulating layer, and a protective layer adapted to protect the substrate from oxidation and/or corrosion, the environmental barrier at least partially covering the substrate, at least one reactive layer being adapted to react with at least one CMAS compound, the reactive layer covering at least part of the environmental barrier. The invention is characterized in that the material of the reactive layer comprises an oxide of formula A′A″BO.sub.5-δ, A′ being selected from a rare earth and yttrium, A″ being selected from a rare earth yttrium and aluminum, B being selected from titanium, zirconium, lufnium, tantlum and niobium, wherein δ is a real number between 0 and 0.5.

Claims

1. A turbine part, comprising a substrate, an environmental barrier and at least one reactive layer, the environmental barrier comprising at least one layer selected from a thermal insulation layer, a sublayer suitable for promoting adhesion between the substrate and the thermal insulation layer, and a protective layer suitable for protecting the substrate from oxidation and/or corrosion, the environmental barrier at least partially covering the substrate, the at least one reactive layer being suitable for reacting with at least one CMAS compound selected from a calcium oxide, a magnesium oxide, an aluminum oxide and a silicon oxide, the reactive layer covering at least a portion of the environmental barrier, wherein the material of the reactive layer comprises an oxide of formula A′A″BO.sub.5+δ, A′ being selected from a rare-earth element and yttrium, A″ being selected from a rare-earth element, yttrium and aluminum, B being selected from titanium, zirconium, hafnium, tantalum and niobium, δ being a real number comprised between 0 and 0.5, wherein the oxide of formula A′A″BO.sub.5+δ having has a rare-earth element atomic fraction comprised between 18% and 25%.

2. The turbine part as claimed in claim 1, wherein the oxide of formula A′A″BO.sub.5+δ has a lattice selected from a cubic lattice, an orthorhombic lattice and a hexagonal lattice.

3. The turbine part as claimed in claim 1, wherein A′ and A″ are the same element.

4. The turbine part as claimed in claim 1, comprising at least two reactive layers, the two reactive layers having at least one different element selected from A′, A″ and B.

5. The turbine part as claimed in claim 1, wherein the oxide is suitable for forming a precipitate comprising apatite upon contact with a CMAS compound selected from a calcium oxide, a magnesium oxide, an aluminum oxide and a silicon oxide.

6. The turbine part as claimed in claim 1, wherein the oxide of formula A′A″BO.sub.5+δ has a crystal lattice having at least one space group of the type selected from Fm3m, Pnma and P6.sub.3/mmc.

7. The turbine part as claimed in claim 1, wherein the reactive layer directly covers a layer selected from the thermal insulation layer and the protective layer.

8. The turbine part as claimed in claim 1, wherein the reactive layer has a thickness comprised between 5 μm and 500 μm.

9. The turbine part as claimed in claim 1, wherein the reactive layer comprises between 5% and 80% by volume of said oxide of formula A′A″BO.sub.5+δ and further comprises at least 10% by volume of an element selected from YSZ, Al.sub.2O.sub.3, Y.sub.2O.sub.3ZrO.sub.2Ta.sub.2O.sub.5, RE.sub.2Zr.sub.2O.sub.7, and RE.sub.2Si.sub.2O.sub.7 and combinations thereof, wherein RE denotes an element selected from yttrium and a lanthanide.

10. The turbine part as claimed in claim 1, wherein the oxide of formula A′A″BO.sub.5+δ is suitable for forming a product upon a first reaction with the CMAS compound, said product being suitable for forming an apatite phase upon a second reaction with the CMAS compound and/or with another product of the first reaction.

11. A process for protecting a turbine part comprising a step of depositing on the turbine part, a reactive layer suitable for reacting with at least one CMAS compound selected from a calcium oxide, a magnesium oxide, an aluminum oxide and a silicon oxide, wherein the material of the reactive layer comprises an oxide of formula A′A″BO.sub.5+δ, A′ being selected from a rare-earth element and yttrium, A″ being selected from a rare-earth element, yttrium, scandium and aluminum, B being selected from titanium, zirconium, hafnium, tantalum and niobium, δ being a real number comprised between 0 and 0.5, the turbine part comprising: a substrate, an environmental barrier comprising at least one layer selected from a thermal insulation layer, a sublayer suitable for promoting adhesion between the substrate and a thermal insulation layer, and a protective layer suitable for protecting the substrate from oxidation and/or corrosion, the environmental barrier at least partially covering the substrate, the reactive layer being deposited on the environmental barrier.

12. The process as claimed in claim 11, wherein the reactive layer is deposited by a method selected from atmospheric-pressure or low-pressure plasma spraying, suspension plasma spraying, solution plasma spraying, high-velocity powder or suspension flame spraying, electron-beam evaporation, vapor deposition, sol-gel and electrophoresis.

Description

DESCRIPTION OF THE FIGURES

[0036] Other features, aims and advantages of the invention will emerge from the following description, which is purely illustrative and non-limiting, and which should be read in conjunction with the appended drawings in which:

[0037] FIG. 1 schematically illustrates a cross-section of a turbine part, for example a turbine blade or a nozzle vane,

[0038] FIG. 2 is a microphotograph illustrating a cross-section of substrate covered with an environmental barrier,

[0039] FIG. 3 is a microphotograph illustrating the insertion of molten CMAS compounds into the environmental barrier,

[0040] FIG. 4 is a microphotograph illustrating the insertion of molten CMAS compounds into the environmental barrier,

[0041] FIG. 5 is a microphotograph illustrating the rupture of an environmental barrier,

[0042] FIG. 6 is a microphotograph illustrating the rupture of an environmental barrier,

[0043] FIG. 7 is a schematic illustration of a turbine part comprising a coating in accordance with the invention,

[0044] FIG. 8 schematically illustrates a turbine part comprising a coating in accordance with the invention, in contact with CMAS compounds,

[0045] FIG. 9 schematically illustrates a turbine part comprising a coating in accordance with the invention.

[0046] Throughout the figures, similar elements bear identical reference marks.

DEFINITIONS

[0047] The term “superalloy” refers to an alloy which, at high temperature and high pressure, has very good resistance to oxidation, corrosion, creep and cyclic stresses (particularly mechanical or thermal stresses). Superalloys have a particular application in the manufacture of parts used in aeronautics, for example turbine blades, because they constitute a family of high-strength alloys that can work at temperatures relatively close to their melting points (typically 0.7 to 0.8 times their melting temperatures).

[0048] A superalloy can have a two-phase microstructure comprising a first phase (called “γ phase”) forming a matrix, and a second phase (called “γ′ phase”) forming precipitates hardening in the matrix. The coexistence of these two phases is referred to as the γ-γ′ phase.

[0049] The “base” of the superalloy refers to the main metal component of the matrix. In most cases, superalloys comprise an iron, cobalt, or nickel base, but sometimes also a titanium or aluminum base. The base of the superalloy is preferentially a nickel base.

[0050] “Nickel-base superalloys” have the advantage of providing a good compromise between oxidation resistance, high-temperature fracture resistance and weight, which justifies their use in the hottest parts of turbojet engines.

[0051] Nickel-base superalloys are made up of a γ phase (or matrix) of the γ-Ni face-centered cubic austenitic type, possibly containing additives in a (Co, Cr, W, Mo)-substituted solid solution, and a γ′ phase (or precipitates) of the γ′-Ni.sub.3X type, with X=Al, Ti or Ta. The γ′ phase has an ordered L12 structure, derived from the face-centered cubic structure, coherent with the matrix, i.e., having an atomic lattice very close thereto.

[0052] The term “volume fraction” refers to the ratio of the volume of an element or a group of elements to the total volume.

[0053] A “space group” of a crystal refers to the set of symmetries of a crystal structure, that is to say the set of affine isometries leaving the structure invariant. It is a group in the mathematical sense of the term. Preferentially, a crystal is organized, in the invention, according to a space group of the type

Fm3m   [Math. 4]

[0054] , a space group of the type

Pnma   [Math. 5]

[0055] and/or a space group of the type

P6.sub.3/mmc   [Math. 6]

DETAILED DESCRIPTION OF THE INVENTION

[0056] With reference to FIG. 7, a part 1 comprises a substrate 2. The substrate 2 may preferentially be a superalloy substrate 2, and preferably a nickel-base superalloy substrate as described above. The substrate is covered, at least in part, by an environmental barrier 3. The environmental barrier 3 may comprise, in a known manner, and as illustrated in FIG. 1, a sublayer 4 extending between the substrate 2 and the other layers of the environmental barrier 3, directly covering the substrate 2, suitable for promoting adhesion between the substrate 2 and the other layers of the environmental barrier 3. The environmental barrier 3 may also comprise a protective layer 5, suitable for protecting the substrate 2 from oxidation and/or corrosion, and directly covering the sublayer 4. The protective layer 5 is, for example, formed by oxidation of the sublayer 4. The protective layer may, for example, be made of alumina. The environmental barrier 3 may also comprise a thermal insulation layer 7, directly covering the protective layer 5.

[0057] The part 1 also comprises a reactive layer 9 suitable for reacting with at least one CMAS compound 8. The CMAS compound 8 may be selected from a calcium oxide, a magnesium oxide, an aluminum oxide and/or a silicon oxide and combinations thereof. The reactive layer 9 at least partially covers the environmental barrier 3. It can directly cover at least one of the layers of the environmental barrier 3, selected from the protective layer 5 and the thermal insulation layer 7. Different reactive layers 9 may also cover different layers of the environmental barrier 3. The embodiment illustrated in FIG. 1 comprises at least one reactive layer 9 covering all of the layers of the environmental barrier 3. The reactive layer 9 can have a thickness comprised between 5 μm and 500 μm, so as to allow the formation of an apatite phase upon contact with a CMAS compound 8.

[0058] The material of the reactive layer 9 comprises an oxide of formula A′A″BO.sub.5+δ, A′ being selected from a rare-earth element and yttrium, A″ being selected from a rare-earth element, yttrium, scandium and aluminum, B being selected from titanium, zirconium, hafnium, tantalum and niobium, δ being a real number comprised between 0 and 0.5. This formula allows the oxide of the reactive layer 9 (hereinafter “the oxide”) to have a volume fraction of rare-earth elements and/or yttrium high enough to allow rapid precipitation of the molten CMAS compound(s), and avoid their introduction into interstices presented in the environmental barrier 3. This formula can also advantageously allow the oxide of the reactive layer 9 to have a cubic lattice. Table 1 comprises the various elements A′, A″ and B that can be selected for the oxide.

TABLE-US-00001 TABLE 1 A′ A″ B Sc, Y, La, Sc, Y, La, Ta, Nb, Ce, Pr, Ce, Pr, Ti, Zr, Hf Nd, Pm, Nd, Pm, Sm, Eu, Sm, Eu, Gd, Tb, Gd, Tb, Dy, Ho, Dy, Ho, Er, Tm, Er, Tm, Yb, Lu Yb, Lu, Al

[0059] Thus, the oxide material can have an atomic fraction of rare-earth elements and/or yttrium, aluminum and scandium comprised between 10% and 25%, and preferentially between 18% and 25% when A′ and A″ are rare-earth elements and/or yttrium. This range of atomic fractions of rare-earth elements and/or yttrium, comprising higher atomic fractions than those of Gd.sub.2Zr.sub.2O.sub.7 for example, allows the reactive layer 9 material to exhibit faster reaction kinetics with CMAS compound(s) 8 than materials described in the prior art (for example Gd.sub.2Zr.sub.2O.sub.7). Thus, the molten CMAS compound(s) 8 in contact with the reactive layer 9 are immobilized faster or are slowed by a production of an apatite phase, thickening and/or solidifying the reactive CMAS compound 8 at the interface with the environmental barrier 3, and avoiding contact between the CMAS compound(s) 8 and other parts of the environmental barrier 3.

[0060] By its composition, the oxide may also have a crystal lattice with a cubic crystal structure, preferentially having a space group of the type

Fm3  [Math. 7]

, and/or a hexagonal type crystal structure, preferentially with a space group

Pnma   [Math. 8]

[0061] , and/or a hexagonal type structure, preferentially with a space group

P6.sub.3/mmc   [Math. 9]

[0062] Advantageously, the elements A′ and A″ may be different. Thus, the reactivity of the oxide with respect to a/the CMAS(s) 8 can be increased by the formation of different phases, comprising at least one apatite phase, for example of formula Ca.sub.2RE.sub.8(SiO.sub.4).sub.6O.sub.2, RE being a rare-earth element or yttrium. One or more secondary oxides may also be produced by the reaction between the oxide and the CMAS compound(s) 8.

[0063] Advantageously, the elements A′, A″, B are selected so as to allow the formation of a secondary oxide, resulting from the reaction between the oxide and the CMAS compound(s) 8. The secondary oxide formed may be reactive to secondary products of the reaction between the oxide and the CMAS compound(s) 8. The secondary oxide formed may also be directly reactive with the CMAS compound 8. The secondary oxides produced may be, for example: [0064] zirconias (ZrO.sub.2) stabilized by lime (CaO) and/or by magnesia (MgO), [0065] hafnium oxides (HfO.sub.2) stabilized by lime (CaO) and/or by magnesia (MgO), [0066] perovskites, such as calcium (CaTiO.sub.3) or magnesium (MgTiO.sub.3) titanates.

[0067] These different secondary oxides can be suitable for forming an apatite phase upon reaction with the CMAS compound(s) 8.

[0068] The elements A′ and A″ may be the same element A: the oxide of the reactive layer 9 may be described by the formula A.sub.2BO.sub.5+δ, δ being a real number comprised between 0 and 0.5. The elements of the oxide are selected from the elements described in Table 2.

TABLE-US-00002 TABLE 2 A B Sc, Y, La, Ta, Nb, Ce, Pr, Ti, Zr, Hf Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu

[0069] Thus, the atomic fraction of rare-earth element or aluminum or scandium or yttrium can be increased compared with the known oxides, due to the oxide structure. The production of the reactive layer 9 can also be simplified in this way.

[0070] Advantageously, the reactive layer 9 may comprise other anti-CMAS oxides. The reactive layer 9 may comprise between 5% and 80% by volume of said oxide and further comprises at least 10% by volume of an element selected from YSZ, Al.sub.2O.sub.3, Y.sub.2O.sub.3—ZrO.sub.2—Ta.sub.2O.sub.5, RE.sub.2Zr.sub.2O.sub.7 and RE.sub.2Si.sub.2O.sub.7 and combinations thereof, where RE denotes an element selected from yttrium and a lanthanide.

[0071] Another aspect of the invention is a process for protecting a part against molten sand(s). The process comprises a step of depositing the reactive layer 9 as described above, on a part 1, or a portion of the part 1. “Portion of the part 1” means a portion of the surface and/or an inner portion of the part 1 (in which case one or more layers of the part 1 may cover the reactive layer 9 once the part 1 is manufactured). After deposition, the part 1 comprises the reactive layer 9. The reactive layer 9 may be deposited directly on the substrate 2 of the part 1, for example a superalloy substrate 2, or on one or more layers of an environmental barrier 3. The deposition of the reactive layer 9 can be performed on at least one of the layers forming the environmental barrier 3, and preferentially on the thermal insulation layer 7. Thus, and unlike known parts, the part 1 comprising the reactive layer 9 deposited on the thermal insulation layer 7 has sufficient reactivity with CMAS compound(s) 8 to produce at least one apatite phase before the insertion of the molten CMAS compound(s) 8 into the interstices of the thermal insulation layer 7, and thus avoid or limit this insertion. In this way, the CMAS compound(s) 8 can have greater difficultly accessing the surface of the environmental barrier 3, and their effect on the breakdown of the environmental barrier 3 is limited.

EXAMPLE

[0072] Reaction between a liquid CMAS 8 and a reactive layer of Gd.sub.2TiO.sub.5

[0073] With reference to FIG. 8, a reactive layer 9 comprising the oxide Gd.sub.2TiO.sub.5 is subjected to chemical attack by a molten CMAS 8. The reactive layer 9 is deposited by suspension plasma spraying (SPS) during the manufacture of the part 1.

[0074] With reference to FIG. 9, after a reaction time of for example more than 5 min, preferentially more than 1 min, a portion of the reactive layer 9 is dissolved by the CMAS compound 8, and an apatite phase Ca.sub.2Gd.sub.8(SiO.sub.4).sub.6O.sub.2 impervious to the molten CMAS 8 is formed between the reactive layer 9 and the molten CMAS 8. The Ca.sub.2Gd.sub.8(SiO.sub.4).sub.6O.sub.2 layer is also impervious to other reaction products (by-products) between the reactive layer 9 and the CMAS 8 compounds. The Ca.sub.2Gd.sub.8(SiO.sub.4).sub.6O.sub.2 layer also allows for the production of secondary phases, thus protecting the reactive layer 9. The environmental barrier 3 has no cracks. Indeed, the cation reservoir of compound A, i.e., A′ and A″ when A′ and A″ are the same element, allows a tight layer to be formed and thus limits the penetration depth, compared with the use of a known reactive layer such as La.sub.2Zr.sub.2O.sub.7.