Patent ID: 8001669
Filing Date: 2011-08-23
Classification: B08B,F01D,F05D,Y10T

Abstract:
1. A method of repairing a turbine engine component, the method comprising the steps of: providing a turbine engine component formed of a composite material, the composite material having a first surface and a second surface, a porous structure extending from the first surface to the second surface, the first surface defining an interior volume of the turbine engine component and the second surface defining an exterior surface of the turbine engine component; sealing the interior volume; exposing the first surface of the interior volume to a first gas pressure and the second surface to a second gas pressure, the first gas pressure higher than the second gas pressure; and using a difference between the first gas pressure and the second gas pressure to pass a cleaning liquid through the porous structure from the first surface to the second surface.