US 10,213,883 B2 · System and method for in situ repair of gas turbine engine casing clearance

Abstract

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

Claims18

Dependent claims

A system for repairing an abradable material coated on a casing of a gas turbine engine, the system comprising:

an articulating guide configured to fit into an access port of the gas turbine engine, the articulating guide comprising a proximal end and a distal end;
a repair tool configured at a distal end of the articulating guide, the repair tool comprising a body having a proximal end and a shaped distal end, the shaped distal end extending away from the body and configured to trench out an area of the abradable material comprising a defect;
and a filler material for filling the trenched out area, wherein the filler material comprises at least one of a resin obtained by room-temperature vulcanization (RTV), rubber, aluminum-bronze with polyester, aluminum-silicone with polyester, or alloy Y and LUCITE.

Dependencies are inferred from the claim text.

System and method for in situ repair of gas turbine engine casing clearance

Life of this patent

System and method for in situ repair of gas turbine engine casing clearance

Life of this patent

Abstract

Claims18