Method for producing a metal bladed element for a turbomachine of an aircraft

Patent metadata

Field	Value
Publication number	US-12084779-B2
Application number	US-201915733743-A
Country	US
Kind code	B2
Filing date	Apr 19, 2019
Priority date	Apr 19, 2018
Publication date	Sep 10, 2024
Grant date	Sep 10, 2024

Abstract

The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the 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 step a).

First claim

The invention claimed is:

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 X 1 , the method comprising the steps of:
a) producing the bladed element by lost-wax casting, the trailing edge having a thickness X 2 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 X 1 which cannot be directly obtained by the step a), the thickness X 1 being less than the thickness X 2 ,
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
FeCl 3 at a concentration of between 300 g/L and 500 g/L.

2. The method according to claim 1 , wherein the thickness X 1 is less than 1 mm.

3. The method according to claim 1 , wherein the chemical milling removes a material thickness at the surface of between 0.05 and 0.5 mm.

4. The method according to claim 1 , wherein the bladed element is made of a metal alloy based on nickel, cobalt or chromium.

5. The method according to claim 4 , wherein it the method comprises at least one subsequent step selected from: a step of inspecting material health, a step of inspecting final dimensioning, and a step of surfacing by tribofinishing.

6. The method according to claim 1 , wherein the bladed element is partially immersed in the bath, wherein the bladed element may comprise masked zones so that they are not milled in contact with the bath.

7. The method according to claim 1 , wherein the bladed element is fully immersed in the bath, wherein the bladed element may comprise masked zones so that they are not milled in contact with the bath.

8. The method according to claim 1 , wherein the step b) comprises a prior step of etching at least part of the bladed element by immersing the bladed element into an etching bath.

9. The method according to claim 1 , wherein the chemical milling bath temperature is of 50° C.

Assignees

• Safran Aircraft Engines
• Safran

Inventors

• Soisson Marc
• Boukerma Said
• Lisowski Janusz
• Gimel Alexandre
• Saboundji Amar

Classifications

• F05D2230/21

  by casting · CPC title

• F05D2230/10

  by removing material · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D5/14

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• B23P15/02

  turbine or like blades from one piece · CPC title