Braze methods and components for turbine buckets
US-2015377037-A1 · Dec 31, 2015 · US
Superalloy turbomachine part with an optimized hafnium content
US12392256B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-12392256-B2 |
| Application number | US-202117797920-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 2, 2021 |
| Priority date | Feb 6, 2020 |
| Publication date | Aug 19, 2025 |
| Grant date | Aug 19, 2025 |
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Abstract
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A turbomachine part includes a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being composed of nickel and unavoidable impurities.
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbomachine part comprising a nickel-based superalloy substrate comprising, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally comprising niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being nickel and unavoidable impurities. 2. The turbomachine part according to claim 1 , wherein the hafnium mass content in the superalloy is between 670 ppm and 780 ppm. 3. The turbomachine part according to claim 1 , wherein the superalloy defines an outer surface of the part. 4. The turbomachine part according to claim 1 , comprising: a substrate formed by the nickel based superalloy, and a β-structured nickel aluminide coating present on the substrate. 5. The turbomachine part according to claim 4 , wherein the β-structured nickel aluminide coating is a β-structured NiAl coating or β-structured NiPtAl coating. 6. The turbomachine part according to claim 4 , wherein a thermal barrier is present on the β-structured nickel aluminide coating. 7. The turbomachine part according to claims 1 , wherein the superalloy is monocrystalline. 8. The turbomachine part according to claims 1 , wherein said part is a turbomachine vane, a turbomachine distributor, a turbomachine turbine ring, or a turbomachine combustion chamber. 9. A turbomachine comprising a part according to claims 1 .
Assignees
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Classifications
Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title
Superalloys · CPC title
Combustors or associated equipment · CPC title
Fluid guiding means, e.g. vanes · CPC title
in gas turbines · CPC title
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- What does patent US12392256B2 cover?
- A turbomachine part includes a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of c…
- Who is the assignee on this patent?
- Safran Aircraft Engines, Safran, Centre Nat Rech Scient, and 1 more
- What technology area does this patent fall under?
- Primary CPC classification F01D25/005. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Aug 19 2025 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).