Method for manufacturing a shell mold for production by lost-wax casting of bladed elements of an aircraft turbine engine

Patent metadata

Field	Value
Publication number	US-9862023-B2
Application number	US-201515324390-A
Country	US
Kind code	B2
Filing date	Jun 29, 2015
Priority date	Jul 7, 2014
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

A method for manufacturing a shell mold for the production by lost-wax casting of bladed elements ( 1 ) of an aircraft turbine engine, including the following steps: creating an assembly ( 200 ) including a wax pattern ( 100 ) as well as a device for forming a cup for pouring metal ( 32 b ) and having an end surface ( 40 a ); depositing a hot wax coating layer on at least one portion of the end surface ( 40 a ); forming the shell mold around the assembly ( 200 ). In addition, the method includes, between steps b) and c), the implementation of a step of structuring the coating layer intended for reinforcing the adhesion between the layer ( 46 ) and the shell mold, and including the production of recesses ( 62 ) and projections ( 60 ) on the still-malleable coating layer.

First claim

The invention claimed is:

1. Method for manufacturing a shell mold for the production by lost-wax casting of a plurality of bladed elements of an aircraft turbine engine, said shell mold in cluster form comprising a plurality of bladed shell mold elements each intended to obtain one of said bladed turbine engine elements, said method comprising the following steps:
a) creating an assembly about which the shell mold is intended to be formed, the assembly including a wax pattern as well as a device for subsequently forming a cup for pouring metal, said device having an end surface;
b) depositing a hot wax coating layer around at least one portion of said assembly, such that said coating layer covers at least one portion of the end surface of the device intended to subsequently form the cup for pouring metal; and
c) forming the shell mold about said assembly;
wherein the method further includes, between steps b) and c), the implementation of a step of structuring the coating layer covering said end surface, this structuring step being intended to reinforce the adhesion between this layer and the shell mold to be formed, and including the production of recesses and projections on the still-malleable coating layer.

2. Method according to claim 1 , wherein the step for structuring the coating layer is implemented by inserting a plurality of imprinting elements in said still-malleable coating layer, causing the formation of said projections about the imprinting elements, then by removing the latter revealing recesses, each surrounded by one of said projections.

3. Method according to claim 2 , wherein the imprinting elements are studs with an external surface head having a general spherical cap shape.

4. Method according to claim 3 , wherein the ratio between the maximum external diameter of each stud, and the external diameter of the end surface of the device, is less than 20.

5. Method according to claim 3 , wherein the number of studs is between 3 and 20.

6. Method according to claim 2 , wherein the step for structuring the coating layer is implemented by applying a pressure from a supporting member bearing the plurality of imprinting elements, against said still-malleable coating layer.

7. Method according to claim 6 , wherein said application of pressure is performed by moving said assembly, against the supporting member remaining stationary.

8. Method according to claim 1 , wherein the step for forming the shell mold about said assembly includes at least one drying operation performed at least in part with said end surface facing downward, and with said shell mold, surrounding the assembly, moved inside a drying station.

9. Method according to claim 1 , wherein the step for forming the shell mold is performed by dip coating.

10. Method for manufacturing by lost-wax casting a plurality of bladed elements of an aircraft turbine engine, wherein the method includes the production of a shell mold using the method according to claim 1 , followed by casting of metal in the shell mold.

Assignees

• Safran Aircraft Engines

Inventors

• Marques François
• Docquois Wilfrid
• Eberschveiller Eric

Classifications

• F05D2220/323

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

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• B22C9/04 Primary

  Use of lost patterns · CPC title

• B22C9/103

  Multipart cores · CPC title

• B05D1/18

  performed by dipping · CPC title