Corrosion mitigation for gearbox

Patent metadata

Field	Value
Publication number	US-10077499-B2
Application number	US-201314073188-A
Country	US
Kind code	B2
Filing date	Nov 6, 2013
Priority date	Nov 6, 2013
Publication date	Sep 18, 2018
Grant date	Sep 18, 2018

Abstract

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

What is claimed is:

1. A method of rebuilding a damaged portion of a groove in a magnesium component, comprising:
forming an area in a sidewall by removing all material exhibiting wear or localized corrosion and pitting, the sidewall defining a portion of a recessed opening located within a central portion of the groove;
creating a deposit in the area, the deposit being integrally formed with the sidewall and an inner surface of a recessed opening of the groove; and
removing any excess material from the deposit.

2. The method according to claim 1 , wherein the magnesium component is a gearbox housing of a rotary wing aircraft.

3. The method according to claim 1 , wherein the deposit includes one or more layers of powdered material applied to the area through a cold spray deposition process.

4. The method according to claim 3 , wherein the powdered material includes aluminum.

5. The method according to claim 1 , wherein the deposit extends from an inner surface of the recessed opening to an outer surface of the sidewall and has a depth configured to completely eliminate all damage from the sidewall.

6. The method according to claim 1 , wherein excess material is removed so that the deposit is substantially flush with an outer surface of sidewall.

7. The method according to claim 1 , wherein excess material is removed so at least one dimension of the magnesium component including the deposit is substantially equal to an original dimension thereof.

8. A method of preemptively forming a deposit in a groove of a magnesium component housing, comprising the steps of:
removing material from a sidewall to form an area, wherein damage is expected to occur in the removed material, the sidewall defining a portion of a recessed opening located within a central portion of the groove;
forming a deposit in the area, the deposit being integrally formed with the sidewall of the magnesium component and an inner surface of the recessed opening; and
removing any excess material from the deposit.

9. The method according to claim 8 , wherein the magnesium component is a gearbox housing of a rotary wing aircraft.

10. The method according to claim 8 , wherein the deposit includes one or more layers of powdered material applied to the area through a cold spray deposition process.

11. The method according to claim 10 , wherein the powdered material includes aluminum.

12. The method according to claim 8 , wherein excess material is removed so that at least one dimension of the magnesium component including the deposit is substantially equal to an original dimension thereof.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Sullivan James
• Guillemette Robert
• Choi Jinkyu
• Petroskey Wayne E
• Hansen Eric K
• Chory Anthony G
• Le Do Young Hanh

Classifications

• Y10T428/24479

  including variation in thickness · CPC title

• C23C4/18

  After-treatment · CPC title

• F16H57/02

  Gearboxes; Mounting gearing therein · CPC title

• C23C4/08

  containing only metal elements (C23C4/073 takes precedence) · CPC title

• F16H2057/02017

  characterised by special features related to the manufacturing of the gear case, e.g. special adaptations for casting · CPC title