| abstract |
A method for in-situ cleaning of compressor blades in a gas turbine engine on an aircraft comprises the following sequential steps:n Step 1—washing said compressor blades by spraying a first liquid composition into the engine; and Step 2—finally rinsing said washed compressor blades by spraying a second liquid composition into the engine,n nwherein the second liquid composition, has a freezing point of −10° C. or below and is non-aqueous and hydrophilic. |