Cleaning solution and methods of cleaning a turbine engine
A cleaning solution for a turbine engine includes water; a first organic acidic component that comprises citric acid; a second organic acidic component that comprises glycolic acid; isopropylamine sulphonate; alcohol ethoxylate; triethanol amine; and sodium lauriminodipropionate. The cleaning solution has a pH value between about 2.5 and about 7.0.
1. A cleaning solution for an in-situ aircraft turbine engine having internal passages and at least some components that have mineral dust accumulated thereon, wherein at least some of the mineral dust has thermally reacted to form CMAS-based reaction products, comprising:
0.21 weight percent citric acid;
0.21 weight percent glycolic acid;
0.14 weight percent isopropylamine sulphonate;
0.07 weight percent alcohol ethoxylate;
0.07 weight percent triethanol amine;
0.03 weight percent monosodium-N-lauryl-B-iminodipropionic acid;
(CH)2N(NH)CH that was added to titrate the cleaning solution to a pH of 5.5;
and wherein a balance of the cleaning solution comprises water
such that when applied to the in-situ aircraft turbine engine, the cleaning solution selectively dissolves interstitial cements and both unreacted sub-layers of the mineral dust accumulations and the CMAS-based reaction products to thereby remove foreign material from the in-situ aircraft turbine engine without pitting corrosion or preferential etching at grain boundaries and without detriment to tensile fracture strength of the in-situ aircraft turbine engine.