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Erosion and fatigue resistant blade and blade coating
US9404172B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9404172-B2 |
| Application number | US-201213633597-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 2, 2012 |
| Priority date | Feb 22, 2012 |
| Publication date | Aug 2, 2016 |
| Grant date | Aug 2, 2016 |
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- Title
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- Abstract
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Abstract
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A coating is described for an airfoil blade component. The coating comprises a cermet material and has, when applied to the rotor blade, a compressive residual stress greater than about 60 ksi. In another embodiment, the compressive residual stress of the coating is in the range of approximately 90-110 ksi.
First claim
Opening claim text (preview).
The invention claimed is: 1. An airfoil blade comprising: an airfoil blade component body comprising a polymer matrix composite and a metal sheath covering the polymer matrix composite; a metallic erosion strip disposed on a leading edge of the airfoil blade component body and comprising opposite terminal strip portions proximate to the leading edge at opposite sides of the airfoil blade component body; and a cermet coating disposed on a leading edge surface of the strip, the cermet coating having a compressive residual stress of about 90-110 ksi and comprising opposite terminal coating portions that are respectively associated with the opposite terminal strip portions and respectively recessed toward the leading edge of the airfoil blade component from the opposite terminal strip portions. 2. The airfoil blade of claim 1 , wherein the cermet is selected from the group consisting of tungsten-carbide-cobalt, tungsten-carbide-nickel, tungsten-carbide-cobalt-chrome, chrome-carbide-nickel-chrome, chrome-carbide-nickel, and combinations thereof. 3. The airfoil blade of claim 1 , wherein the metallic erosion strip comprises nickel or titanium. 4. The airfoil blade of claim 1 , wherein the strip has a uniform thickness and the cermet coating has an increasing thickness toward the leading edge of the airfoil blade component. 5. The airfoil blade of claim 1 , wherein said cermet coating is disposed along substantially the entire leading edge of the airfoil blade. 6. The airfoil blade of claim 1 , wherein the airfoil blade is a helicopter rotor blade. 7. The airfoil blade of claim 6 , wherein said cermet coating is disposed on the surface of the strip on a leading edge portion of the airfoil blade closer to its axis of rotation than another leading edge portion of the airfoil blade.
Assignees
Inventors
Classifications
Cross-Sectional Technologies · mapped topic
Impact or kinetic deposition of particles · CPC title
related to the leading edge of a rotor blade · CPC title
for protecting blades, e.g. coating · CPC title
- C23C4/06Primary
Metallic material · CPC title
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Frequently asked questions
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- What does patent US9404172B2 cover?
- A coating is described for an airfoil blade component. The coating comprises a cermet material and has, when applied to the rotor blade, a compressive residual stress greater than about 60 ksi. In another embodiment, the compressive residual stress of the coating is in the range of approximately 90-110 ksi.
- Who is the assignee on this patent?
- Clavette Patrick Louis, Shi Jun, Nardi Aaron T, and 1 more
- What technology area does this patent fall under?
- Primary CPC classification C23C4/06. Mapped technology areas include Chemistry & Metallurgy.
- When was this patent published?
- Publication date Tue Aug 02 2016 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).