Systems, formulations, and methods for removal of ceramic cores from turbine blades after casting

1. A method comprising:

placing a metallic aircraft part having a ceramic material disposed therein into a vessel;

placing a solution into the vessel, the solution comprising:

a strong base; and

a corrosion inhibitor,

wherein the strong base is an alkali metal hydroxide,

wherein the corrosion inhibitor is at least one of an organic acid having a-COOH functional group or an alkali metal salt of one of an organic acid having a-COOH functional group, and

wherein the corrosion inhibitor is at least one of tartaric acid, sodium tartrate, citric acid, acetic acid, oxalic acid, malic acid, maleic acid, lactic acid, glycine, L-histidine, or DETPA (Diethylenetriaminepentaacetate),

wherein the strong base has a first concentration of between 5.54M to 11.09M.

2. The method of claim 1 , further comprising heating the vessel to an elevated temperature.

3. The method of claim 2 , further comprising increasing the pressure within the vessel to above atmospheric pressure.

4. The method of claim 3 , further comprising holding the vessel at the elevated temperature and above atmospheric pressure for between four hours and ninety six hours.

5. The method of claim 3 , further comprising holding the vessel at the elevated temperature and above atmospheric pressure until substantially all the ceramic material has dissolved.

6. The method of claim 3 , wherein the strong base is at least one of sodium hydroxide or potassium hydroxide.

7. The method of claim 1 , further comprising a solubility enhancer wherein the solubility enhancer is Ethylenediaminetetraacetic acid (EDTA).

8. The method of claim 7 , wherein the strong base is KOH.

9. The method of claim 8 , wherein the corrosion inhibitor is sodium tartrate, wherein the sodium tartrate has a second concentration of between 1 mg/L and 100 g/L.