CPC C23F 1/04 (2013.01) [B22C 9/10 (2013.01); B22C 9/24 (2013.01); B23P 15/02 (2013.01); F01D 5/14 (2013.01); B22C 7/02 (2013.01); F05D 2220/323 (2013.01); F05D 2230/10 (2013.01); F05D 2230/21 (2013.01)] | 9 Claims |
1. A method for producing a metal bladed element for an aircraft turbine engine, this bladed element comprising at least one blade comprising a pressure side and a suction side extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, the method comprising the steps of:
a) producing the bladed element by lost-wax casting, the trailing edge having a thickness X2 during the step a),
b) finishing the bladed element,
wherein the step b) comprises a chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by the step a), the thickness X1 being less than the thickness X2,
wherein the chemical milling is carried out by immersing the bladed element in a chemical milling bath for a period of between 10 and 300 minutes, the chemical milling bath temperature being between 20 and 70° C.,
wherein the chemical milling bath is water based and comprises:
HCl in a concentration of between 25 g/L to 45 g/L, and
FeCl3 at a concentration of between 300 g/L and 500 g/L.
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