Coated articles and manufacture methods

Abstract

An article (50; 100) has a metallic substrate (22), a bondcoat (30) atop the substrate, and a thermal barrier coating (28; 27, 28) atop the bondcoat. The thermal barrier coating or a layer thereof comprises didymium oxide and zirconia.

Claims

1. An article comprising: a metallic substrate; a bondcoat atop the substrate; and a thermal barrier coating atop the bondcoat, wherein: the thermal barrier coating or a layer thereof comprises: didymium oxide; and zirconia; and the article is a vane or a blade.

2. The article of claim 1 wherein: the didymium oxide in said thermal barrier coating or layer thereof is at a concentration of at least one of 15-60 mole present and 32-80 weight percent; and the zirconia in said thermal barrier coating or layer thereof is at a concentration of at least one of 85-40 mole percent and 20-68 weight percent.

3. The article of claim 1 wherein: the didymium oxide in said thermal barrier coating or layer thereof is at a concentration of at least one of 25-35 mole percent and 47-59 weight percent; and the zirconia in said thermal barrier coating or layer thereof is at a concentration of at least one of 65-75 mole and 41-53 weight percent.

4. The article of claim 1 wherein: the thermal barrier coating or layer thereof has a characteristic thickness of at least 25 micrometers; and the bondcoat has a characteristic thickness of at least 20 micrometers.

5. The article of claim 1 wherein: the substrate comprises a nickel-based superalloy.

6. The article of claim 1 wherein: the article is a gas turbine engine component.

7. The article of claim 1 wherein: the thermal conductivity of the thermal barrier coating is between 0.8 and 1.2 (W m-1 K-1).

8. The article of claim 1 wherein: the thermal barrier coating possesses resistance to molten silicate, CMAS, and salts.

9. The article of claim 1 wherein: the thermal barrier coating comprises: said layer of the thermal barrier coating; and at least one YSZ layer between the bondcoat and said layer.

10. The article of claim 9 wherein: the thermal barrier coating comprises a plurality of said layers alternating with a plurality of said at least one YSZ layer.

11. A method for manufacturing the article of claim 1, the method comprising: applying the bondcoat; and applying the didymium oxide and the zirconia forming didymium zirconate.

12. The method of claim 11 wherein: the applying the didymium oxide and the zirconia comprises mixing and forming an ingot and vaporizing the ingot.

13. The method of claim 11 further comprising: the applying the didymium oxide and the zirconia comprises EB-PVD.

14. The method of claim 11 wherein the combination consists essentially of praseodymium oxide, neodymium oxide and zirconia.

15. The article of claim 1 being said vane.

16. The article of claim 1 being said blade.

17. An article comprising: a metallic substrate; a bondcoat atop the substrate; and a thermal barrier coating atop the bondcoat, wherein the thermal barrier coating or a layer thereof comprises: didymium oxide; and zirconia wherein: the thermal barrier coating comprises: said layer of the thermal barrier coating; and at least one YSZ layer between the bondcoat and said layer; and the thermal barrier coating further comprises: a mixed phase field of fluorite and pyrochlore crystal structure-rare earth zirconate A.sub.2B.sub.2O.sub.7 between said layer and said at least one YSZ layer.

18. A method for coating an article, the method comprising: applying a bondcoat; and applying a combination of didymium oxide and zirconia forming didymium zirconate and wherein the article is a vane or a blade.

19. The method of claim 18 wherein the article is said blade.

20. A method for coating an article, the method comprising: applying a bondcoat; and applying a combination of praseodymium oxide, neodymium oxide and zirconia forming zirconate and wherein the article is a vane or a blade.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a partially schematic sectional view of substrate having a thermal barrier coating (TBC).

(2) FIG. 2 is a partially schematic view of a vane bearing the TBC.

(3) FIG. 3 is a partially schematic view of a blade bearing the TBC.

(4) FIG. 4 is a flowchart of a process for coating the substrate of FIG. 1.

(5) FIG. 5 is a partially schematic sectional view of substrate having a second thermal barrier coating (TBC).

(6) FIG. 6 is a partially schematic sectional view of substrate having a third thermal barrier coating (TBC).

(7) FIG. 7 is a partially schematic sectional view of substrate having a fourth thermal barrier coating (TBC).

(8) Like reference numbers and designations in the various drawings indicate like elements.

DETAILED DESCRIPTION

(9) FIG. 1 shows a thermal barrier coating system 20 atop a metallic substrate 22. In an exemplary embodiment, the substrate is a nickel-based superalloy or a cobalt-based superalloy such as a cast component (e.g., a single crystal casting) of a gas turbine engine. Exemplary components are hot section components such as combustor panels, turbine blades, turbine vanes, and air seals.

(10) Exemplary substrate compositional ranges are shown in Table I:

(11) TABLE-US-00001 TABLE I Exemplary Superalloy Compositions Alloy Cr Co C Ti Al W Mo Nb Hf Ta Re Ni Broad Min 3 0 0 0 4 3 0 0 0 6 0 Balance Range Max 12 15 0.045 10 7 10 3 1 0.8 12 5 Balance Example 5 10 5.6 6.0 2.0 0.1 9.0 3.1 Balance

(12) In some embodiments of the materials in Table I (and Tables II and III below), the materials may consist essentially of the listed elements (e.g., with at most trace amounts of other elements). In some embodiments, other elements may be present in individual quantities less than 2.0 weight percent and/or aggregate quantities less than 5.0 weight percent, more narrowly 1.0 weight percent individually and 2.0 weight percent aggregate.

(13) The coating system 20 may include a bondcoat 30 atop a surface 26 of the substrate 22 and a thermal barrier coating (TBC) system 28 atop the bondcoat. A thermally grown oxide (TGO) layer 24 may form at the interface of the bondcoat to the TBC. The exemplary bondcoat is a single-layer bondcoat. Alternatives may have two or more layers. In the exemplary system, the bondcoat consists of or consists essentially of the single layer (e.g., subject to relatively small gradation/transition with each other and with the TBC as noted above).

(14) The exemplary TBC is also a single-layer TBC. Alternatives may involve a multi-layer TBC with at least two layers. In the exemplary system, the TBC consists of or consists essentially of the single layer (e.g., subject to relatively small gradation/transition the bondcoat as noted above).

(15) FIG. 2 shows a vane 50 comprising the cast metallic substrate 22. The vane includes an airfoil 52 having a surface comprising a leading edge 54, a trailing edge 56, a pressure side 58, and a suction side 60. The airfoil extends from an inboard end at a platform or band segment 62 to an outboard end and an outboard shroud or band segment 64. The segments 62 and 64 have respective gaspath surfaces 66 and 68. These are essentially normal to the airfoil surfaces. The TBC system extends at least along the surface of the airfoil and the surfaces 66 and 68.

(16) FIG. 3 shows a blade 100 having an airfoil 102 extending outward from a platform 104. The blade includes an attachment root 106 inboard of the platform. The platform 104 has an outboard gaspath surface 108.

(17) The exemplary bondcoat 30 is an overlay MCrAlY bondcoat. An exemplary MCrAlY overlay bondcoat is a NiCoCrAlYHfSi. Alternative bondcoats are diffusion aluminides or platinum aluminides. Table II provides exemplary bondcoat compositions:

(18) TABLE-US-00002 TABLE II Exemplary MCrAlY Compositions Range Cr Co Mo W Ta Re Al Y Si Hf Zr Ni Broad Min 4 6 0 1 1 0 2 0 0 0 0 Bal. Max 20 25 2 10 10 2 14 2 1 2 2 Bal. Intermediate Min 8 10 0.1 3 3 0.2 4 0.2 0.2 0.2 0 Bal. Max 12 14 2 6 6 0 8 1 1 1 0.5 Bal. Example 1 Highly Alloyed 10 12 1 4.5 4.5 1 6 0.5 0.5 0.5 .25 Bal Metallic Coating Example 2 NiCrAlY 19.5 12.5 0.45 Bal. Example 3 NiCoCrAlY 18 23 12.5 0.3 Bal. Example 4 NiCoCrAlYHfSi 17 22 12.5 0.6 0.4 0.3 Bal.

(19) Exemplary bondcoat thicknesses are 2-500 micrometers, more narrowly, 12-250 micrometers or 25-150 micrometers on average.

(20) The exemplary TBC provides a mixture didymium oxide zirconate. Table III shows two nominal commercially recorded compositions for didymium oxides:

(21) TABLE-US-00003 TABLE III Exemplary Didymium Oxide compositions Weight Percent (wt %) Molecular Weight Range Pr.sub.6O.sub.11 Nd.sub.2O.sub.3 (grams) Broad Min 10 90 Max 40 60 Narrow Min 15 85 Max 30 70 Didymium Oxide 1 25 75 334.8 Didymium Oxide 2 20 80 335.1

(22) Two ranges of different breadths are also given. The broad range in Table III encompasses the chemical variations in monazite deposits in placer deposits from around the world. The narrow range is typical of what is extracted from active mining facilities. The two nominal commercial compositions are derived from the products of heavy mineral sands from two different monazite deposits. While similar in nominal composition, there are enough differences in the derived typical nominal chemistry that they can be considered to be different products and one or the other may have more beneficial properties in a given situation. Thus, the ranges are given to encompass both. In a first example, the FIG. 1 TBC comprises 15-60 molar percent didymium oxide. The majority of the remainder, preferably essentially all of the remainder (e.g., 95% or more by weight) being zirconia. A more particular range composition is 25-35 molar percent didymium oxide with a similar balance zirconia. This may be applied EB-PVD or other appropriate process resulting in the formation of a rare earth zirconate. A rare earth zirconate the term used to describe the alloyed mixture of the rare earth oxide and zirconia. It is commonly used in reference to the line compound of the composition M.sub.2Zr.sub.2O7 (i.e. Gd.sub.2Zr.sub.2O7-gadolinium zirconate). More broadly it can be used to describe the solid solution of the desired metal oxide, M.sub.2O.sub.3 in conjunction with zirconia, (ZrO.sub.2). Exemplary TBC layer thickness is in excess of 25 micrometers, more particularly, in excess of 50 micrometers or 25-130 micrometers.

(23) Exemplary deposition methods include plasma spray deposition and electron beam physical vapor deposition (EB-PVD). FIG. 4 shows an exemplary process with several branches showing several variations including three exemplary plasma spray variations and one exemplary EB-PVD variation. In the EB-PVD variation 402, an appropriate amount of didymium oxide is weighed 410. It is then mixed 412 with zirconium oxides. The mixed powder is then ground 414. The ground powders are then mixed 416 with binder. The mixed powder/binder is then pressed 418 into an ingot. The ingot is then sintered 420. The sintered ingot is then used in EB-PVD coating 422 in a conventional manner.

(24) In a first plasma spray variation 432, the weighing, mixing, and grinding may be performed but then the mixed/ground powders are then mixed 440 with binder and water to form a slurry. The slurry is spray dried 442 to form powders. The dried powders are screened 444. The screened powders are sintered 446. The sintered powders may be plasma sprayed 448 in conventional form. A second plasma spray variation 452 branches off earlier after the weighing of didymium oxide ore. The didymium oxide ore is added 460 with concentrated nitric acid to a reflux reactor. The reactor is heated 462 (e.g., to 100 C. to 250 C.) to dissolve the didymium oxide ore.

(25) The reacted product is then distilled 464 to form didymium nitrate. Amounts of didymium nitrate and a soluble zirconium salt powders are then weighed 466. The powders are dissolved 468 (e.g., in deionized water). Ammonium hydroxide is then titrated 470 into solution. The resulting precipitate is filtered 472 into a cake. The cake is dried and calcined 474. The dried and calcined cake forms a powder which is mixed 476 with solvent and dispersant which may then be plasma sprayed.

(26) In a further variation 480, after the dissolving 468 the solution is filtered 490 and the filtered solution may directly be plasma sprayed.

(27) FIG. 5 shows a two-layer thermal barrier coating system. An underlayer 27 comprises or consists essentially of yttria-stabilized zirconia (e.g., 4-25 weight percent yttria, or more particularly, 6-12 percent or a nominal 7 percent). A second layer 28 (e.g., an outer layer) is deposited atop the underlayer and has the composition noted for the FIG. 1 example. Exemplary YSZ layer thickness is at least 25 micrometer. Exemplary didymium oxide zirconate layer thickness is at least 25 micrometers.

(28) FIG. 6 shows a system otherwise similar to the FIG. 5 system but wherein a third layer 25 intervenes between the YSZ underlayer 27 and the didymium oxide-zirconia layer 28. The exemplary intervening layer 25 is a flourite/pyrochlore zirconate A.sub.2B.sub.2O.sub.7. This layer may be characterized as a stabilized zirconia coating comprising an oxide of La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Mg, Ca, Hf, Sr, 5-60 mol %, more narrowly, 25-35%. Exemplary thickness of the intervening layer is at least 25 micrometers, more particularly 25-130 micrometers.

(29) FIG. 7 shows an alternative embodiment where there are alternating layers: YSZ layers 27-1, 27-2; and the didymium oxide-zirconia layers 28-1, 28-2 (two pairs being shown but more being possible). Exemplary thicknesses of each layer are in excess of 25 micrometers, more particularly 25-130 micrometers. Exemplary overall thickness may be in the overall range above.

(30) The use of first, second, and the like in the following claims is for differentiation within the claim only and does not necessarily indicate relative or absolute importance or temporal order. Similarly, the identification in a claim of one element as first (or the like) does not preclude such first element from identifying an element that is referred to as second (or the like) in another claim or in the description.

(31) Where a measure is given in English units followed by a parenthetical containing SI or other units, the parenthetical's units are a conversion and should not imply a degree of precision not found in the English units.

(32) One or more embodiments have been described. Nevertheless, it will be understood that various modifications may be made. For example, when applied to an existing basic article configuration, details of such configuration or its associated engine may influence details of particular implementations. Accordingly, other embodiments are within the scope of the following claims.