In situ gas turbine prevention of crack growth progression
AssigneeGeneral Electric Company
InventorsHerbert Chidsey Roberts, David Scott Diwinsky, Wayne R. Grady
Life of this patent
Estimating the term…
Abstract
Methods for remotely joining material a surface area of a component of a gas turbine engine are provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning a tip of the integrated repair interface adjacent to a defect defined within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface of the component; and supplying a new material to the area to fill the defect.
Claims17
A method of supplying material to a defective area in a component in a gas turbine engine,
- the method comprising:
- inserting a repair tool through an access port of a gas turbine engine;
- positioning a tip of the repair tool adjacent to a defective area of the component;
- temporarily attaching the tip of the repair tool to a surface of the component at a location adjacent to the defective area of the component;
- and
- supplying a new material to the defective area to repair a defect in the defective area, the new material supplied using the repair tool, wherein the new material comprises a liquid metal, and
- wherein supplying the new material to the defective area comprises:
- supplying the liquid metal from a material supply end of the repair tool to the tip of the repair tool;
- and
- expelling the liquid metal from the tip of the repair tool in a direction of the defect, and
- wherein the repair tool comprises a high temperature conduit extending lengthwise between the material supply end of the repair tool and the tip of the repair tool,
- and wherein supplying the liquid metal from the material supply end of the repair tool to the tip of the repair tool comprises supplying the liquid metal through the high temperature conduit.
Dependencies are inferred from the claim text.