Braze methods and components with heat resistant materials
Braze methods include providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. Braze methods further include at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, and heating the pre-sintered preform on the substrate.
1. A braze method for a turbine shroud onto a substrate, the method comprising:
providing a substrate comprising a pre-sintered preform disposed thereon, the substrate comprising a plurality of Z-notches, a plurality of Z-notch contact surfaces and a plurality of non-Z-notch contact surfaces, the plurality of non-z-notch contact surfaces comprising one or more seal rails, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy, the pre-sintered preform comprising a shape matching the plurality of non-z-notch contact surfaces and the one or more seal rails;
at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, the heat resistant material reducing dimensional instability of the pre-sintered preform during subsequent heat applications of pre-sintered preform; and,
heating the pre-sintered preform on the substrate.
2. The braze method of claim 1 , wherein the heat resistant material comprises a separate pre-sintered preform.
3. The braze method of claim 2 , wherein the separate pre-sintered preform comprises a base alloy and a second alloy, wherein the base alloy comprises a compositional range of, by weight, about 27.0 to 30.0% molybdenum, 16.5 to 18.5% chromium, 3.0 to 3.8% silicon, up to 1.5% iron, up to 1.5% nickel, up to 0.15% oxygen, up to 0.08% carbon, up to 0.03% phosphorus, up to 0.03% sulfur, and the balance cobalt, and wherein the second alloy comprises a compositional range of, by weight, about 22.9 to 24.75% chromium, 9.0 to 11.0% nickel, 6.5 to 7.6% tungsten, 3.0 to 4.0 percent tantalum, 2.6 to 3.16% boron, 0.55 to 0.65% carbon, 0.3 to about 0.6% zirconium, 0.15 to 0.3% titanium, up to 1.3% iron, up to 0.4% silicon, up to 0.1% manganese, up to 0.02% sulfur and the balance cobalt.
4. The braze method of claim 2 , wherein the separate pre-sintered preform comprises, by weight, from about 90 to about 95% base alloy and from about 5 to about 10% second alloy.
5. The braze method of claim 1 , wherein the heat resistant material comprises a powder material coating.
6. The braze method of claim 5 , wherein the powder material coating comprises a compositional range of, by weight, about 27.0 to 30.0% molybdenum, 16.5 to 18.5% chromium, 3.0 to 3.8% silicon, up to 1.5% iron, up to 1.5% nickel, up to 0.15% oxygen, up to 0.08% carbon, up to 0.03% phosphorus, up to 0.03% sulfur, and the balance cobalt.
7. The braze method of claim 1 , wherein the heat resistant material comprises a braze material.
8. The braze method of claim 1 , wherein the heat resistant material comprises a ceramic paint.
9. The braze method of claim 1 , wherein the substrate comprises a turbine bucket shroud.
10. The braze method of claim 9 , wherein the pre-sintered preform is disposed in a cooling channel of the turbine bucket shroud.
11. The braze method of claim 1 , wherein the substrate comprises a nickel-, cobalt, or iron-based superalloy.