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US 8,776,370 B2Granted
Method of maintaining gas turbine engine components
AssigneeUnited Technologies Corporation
InventorsAlexander V. Staroselsky, Richard Pettit
Life of this patent
Estimating the term…
Abstract
An example method of maintaining a serviceable component of a gas turbine engine includes selecting a used component, using a fluid to move an abrasive against a surface of the used component, and removing material from the used component using the abrasive. In one example, the method moves the abrasive against the surface of the used component when the used component is installed within the gas turbine engine.
Claims15
A method of maintaining a serviceable component of a gas turbine engine, comprising:
- selecting a used component;
- moving a fluid that entrains an abrasive material against a surface of the used component;
- removing material from the used component using the abrasive material that is in contact with the surface of the used component, wherein the step of removing smooths the surface of the used component that is in contact with the abrasive material;
- and
- moving the fluid against the surface by operating the gas turbine engine to circulate the fluid,
- wherein the used component defines a film cooling hole having an exit with an edge curvature radius, and the step of removing reduces the edge curvature radius to reduce material stress,
- wherein the used component is attached to the gas turbine engine in an installed position during the step of moving the fluid and the step of removing material.
4 more elements
A method of maintaining a serviceable component of a gas turbine engine, comprising:
- selecting a used component having a fatigued surface;
- moving a fluid that entrains an abrasive material against the fatigued surface;
- lessening variations between extrusions of the fatigued surface and intrusions of the fatigued surface by removing material from fatigued surface using the abrasive material;
- and
- moving the fluid against the fatigued surface by operating the gas turbine engine to circulate the fluid,
- wherein the used component defines a film cooling hole having an exit with an edge curvature radius, and the step of removing reduces the edge curvature radius,
- wherein the used component is in an installed position within the gas turbine engine during the moving.
4 more elements
Dependencies are inferred from the claim text.