Method for reducing adhesive damage due to loss of lubrication in aerospace piston rings
AssigneeRtx Corporation
InventorMary E. Makowiec
Life of this patent
Estimating the term…
Abstract
An aerospace piston seal ring including a body shaped as an annular ring, the body defines an axis centered within the body; a sealing surface extending radially relative to the axis between an inner diameter and an outer diameter; and a surface feature formed along the sealing surface, the surface feature configured as an interruption in the sealing surface, wherein the surface feature is configured to contain a lubricant.
Claims20
An aerospace piston seal ring comprising:
- a body shaped as an annular ring, the body defines an axis centered within the body;
- a sealing surface extending radially relative to the axis between an inner diameter and an outer diameter;
- and
- a surface feature formed along the sealing surface, the surface feature configured as an interruption in the sealing surface, wherein the surface feature is configured to contain a lubricant, wherein the sealing surface is configured to contact with a seal seat of a component of a gas turbine engine.
(canceled)
An aerospace piston seal ring for a gas turbine engine comprising:
- a body shaped as an annular ring, the body defines an axis centered within the body;
- a sealing surface extending radially relative to the axis between an inner diameter and an outer diameter;
- and
- a surface feature formed along the sealing surface, the surface feature configured as an interruption in the sealing surface, wherein the surface feature is configured to contain a lubricant, wherein the surface feature comprises a well for the lubricant to build up to aid in lubrication of the sealing surface to prevent galling between the sealing surface and a component of the gas turbine engine contacting the sealing surface.
A process for lubrication of an aerospace piston seal ring for a gas turbine engine comprising:
- forming a body shaped as an annular ring, the body defines an axis centered within the body;
- forming a sealing surface extending radially relative to the axis between an inner diameter and an outer diameter;
- and
- forming a surface feature along the sealing surface;
- configuring the surface feature as an interruption in the sealing surface;
- configuring the surface feature to contain a lubricant, wherein the surface feature comprises a well for the lubricant to build up to aid in lubrication of the sealing surface;
- and
- preventing galling between the sealing surface and a component of the gas turbine engine contacting the sealing surface.
Dependencies are inferred from the claim text.