Method for manufacturing a core for moulding a blade

Patent metadata

Field	Value
Publication number	US-9981308-B2
Application number	US-201515323300-A
Country	US
Kind code	B2
Filing date	Jun 29, 2015
Priority date	Jun 30, 2014
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

A method of manufacturing a core for molding a blade of a turbomachine, including placing a flexible ceramic sheet in a cavity of a mold in such a way as to shape the ceramic sheet, introducing a ceramic paste into the cavity of the mold, the ceramic paste forming at least one frame in contact with the ceramic sheet, and co-sintering the ceramic sheet and the frame in such a way as to rigidly join together the ceramic sheet and the frame, the frame maintaining the shape of the ceramic sheet given by the mold during the preceding co-sintering phases.

First claim

The invention claimed is:

1. A method for manufacturing a core for casting a blade of a turbine engine, comprising steps of:
placing a flexible ceramic sheet in a cavity of a mold so as to shape the ceramic sheet,
introducing a ceramic paste into the cavity of the mold, the ceramic paste forming at least one frame in contact with the ceramic sheet, and
co-sintering the ceramic sheet and the frame so as to secure the ceramic sheet and the frame together, the frame maintaining the shape of the ceramic sheet given by the mold during the steps preceding co-sintering.

2. The method according to claim 1 , comprising a preliminary step of:
cutting out recess patterns in the ceramic sheet.

3. The method according to claim 2 , wherein the recess patterns have a rectangular, triangular and/or sinusoidal shape.

4. The method according to claim 2 , wherein the space between two successive recess patterns is less than 5 millimeters.

5. The method according to claim 1 , wherein the ceramic sheet comprises silica and alumina.

6. The method according to claim 1 , wherein the ceramic paste forming the frame comprises silica and zircon.

7. The method according to claim 1 , wherein the ceramic sheet has a Young's modulus of less than 5 GigaPascals.

8. The method according to claim 1 , wherein the ceramic sheet has a thickness comprised between 0.04 millimeters and 0.5 millimeters.

9. A method for manufacturing a turbine engine blade comprising:
obtaining the core using the method of claim 1 ; and
casting the blade in a mold containing the core.

Assignees

• Safran Aircraft Engines

Inventors

• Digard Brou De Cuissart Sebastien
• Dujol Charlotte Marie
• Eneau Patrice
• Metron Philippe
• Vollebregt Matthieu Jean-Luc

Classifications

• B22C9/24

  for hollow articles · CPC title

• B22C9/10 Primary

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title

• B22C9/12

  Treating moulds or cores, e.g. drying, hardening · CPC title

• B28B11/04

  for coating {or applying engobing layers}(glazing, engobing C04B) · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title