CPC F01D 25/002 (2013.01) [F02C 7/30 (2013.01); F05D 2230/80 (2013.01)] | 16 Claims |
1. A method of repairing a component of a gas turbine engine in situ, the component comprising a deposit, the method comprising:
directing an insertion tube into an interior of the gas turbine engine such that a distal end of the insertion tube is positioned proximate the component; and
providing a heated flow of gas through the insertion tube to heat the component,
wherein providing the flow of gas through the insertion tube comprises providing the heated flow of gas through the insertion tube at a temperature greater than about 500 degrees Fahrenheit and less than about 1200 degrees Fahrenheit.
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