Damage Mitigation For Gearbox
US-2017299040-A1 · Oct 19, 2017 · US
Corrosion mitigation for gearbox
US10883178B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10883178-B2 |
| Application number | US-201816037658-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 17, 2018 |
| Priority date | Nov 6, 2013 |
| Publication date | Jan 5, 2021 |
| Grant date | Jan 5, 2021 |
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- Title
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- Abstract
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- Assignees and inventors
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Abstract
Official abstract text for this publication.
A magnesium component of a rotary wing aircraft is provided including a groove including a first sidewall and a second sidewall arranged on opposing sides of a recessed opening. The first sidewall includes a deposit positioned adjacent the recessed opening. The deposit is formed by cold spraying one or more layers or powdered material within an area of the first sidewall from which material was removed.
First claim
Opening claim text (preview).
What is claimed is: 1. A magnesium component of a rotary wing aircraft comprising: a groove including a recessed opening located within a central portion of the groove and a first sidewall and a second sidewall arranged on opposing sides of the recessed opening, wherein the first sidewall includes an area from which material of the first sidewall was removed, wherein the area extends to the recessed opening; and a deposit arranged within the area adjacent the recessed opening, the deposit being integrally formed with the first sidewall by cold spraying one or more layers of powdered material within the area of the first sidewall from which material of the first sidewall was removed, wherein the deposit is substantially identical in size and shape to the area from which material of the first sidewall was removed. 2. The magnesium component according to claim 1 , wherein the magnesium component is a gearbox housing. 3. The magnesium component according to claim 1 , wherein the powdered material includes aluminum. 4. The magnesium component according to claim 1 , wherein damage is expected to occur to the area of the sidewall where the deposit is located. 5. The magnesium component according to claim 1 , wherein the deposit extends from an inner surface of the recessed opening to an outer surface of the sidewall. 6. The magnesium component according to claim 1 , wherein the magnesium component including the deposit has at least one dimension substantially equal to an original dimension of the magnesium component. 7. The magnesium component according to claim 6 , wherein the deposit is substantially flush with a remainder of the sidewall.
Assignees
Inventors
Classifications
including variation in thickness · CPC title
Gearboxes; Mounting gearing therein · CPC title
- C23C24/04Primary
Impact or kinetic deposition of particles · CPC title
containing only metal elements (C23C4/073 takes precedence) · CPC title
characterised by special features related to the manufacturing of the gear case, e.g. special adaptations for casting · CPC title
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- What does patent US10883178B2 cover?
- A magnesium component of a rotary wing aircraft is provided including a groove including a first sidewall and a second sidewall arranged on opposing sides of a recessed opening. The first sidewall includes a deposit positioned adjacent the recessed opening. The deposit is formed by cold spraying one or more layers or powdered material within an area of the first sidewall from which material was…
- Who is the assignee on this patent?
- Sikorsky Aircraft Corp
- What technology area does this patent fall under?
- Primary CPC classification C23C24/04. Mapped technology areas include Chemistry & Metallurgy.
- When was this patent published?
- Publication date Tue Jan 05 2021 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 4 related publications on this page (citations in our corpus or others sharing the same primary CPC).