Compacting and injection mold for a fiber preform for fabricating a turbine engine guide vane made of composite material

Patent metadata

Field	Value
Publication number	US-10239241-B2
Application number	US-201715691024-A
Country	US
Kind code	B2
Filing date	Aug 30, 2017
Priority date	May 10, 2011
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers, compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted, and closure blocks arranged inside the trough. Each closure block has a surface pressing normally against a surface of a compacting block and does not have a surface in contact with the fiber preform.

First claim

The invention claimed is:

1. A method of assembling a compacting and injection mold comprising a shell forming a trough that is to receive a fiber preform and that is closed by substantially plane bottom and top covers; compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted; and closure blocks arranged inside the trough, each closure block having a surface pressing normally against a surface of a compacting block and not having a surface in contact with the fiber preform, the method comprising the following steps in succession:
a) assembling the bottom cover in leaktight manner on the trough;
b) positioning the fiber preform that is for use in fabricating a turbomachine part together with the compacting blocks inside the trough;
c) positioning the closure blocks inside the trough; and
d) assembling the top cover in leaktight manner on side walls of the trough.

2. The method according to claim 1 , wherein presser devices for applying normal forces on the compacting blocks are positioned inside the trough prior to positioning the closure blocks.

3. The method according to claim 1 , wherein holder bars are positioned on some of the compacting blocks prior to assembling the top cover on the trough.

4. The method according to claim 1 , wherein the fiber preform is for fabricating a turbine engine vane including an airfoil having a pressure side and a suction side, a top platform at a radially outer end of the airfoil, and a bottom platform at a radially inner end of the airfoil, the bottom platform including an upstream flange at an upstream end thereof and a downstream flange at a downstream end thereof, and
wherein the compacting blocks include
a first compacting block having a surface for pressing normally against a surface of the fiber preform constituting the pressure side of the airfoil of the vane,
a second compacting block having a surface for pressing normally against a surface of the fiber preform constituting the suction side of the airfoil of the vane,
a third compacting block having a surface for pressing normally against a surface of the fiber preform constituting the top platform of the vane,
a fourth compacting block having a surface for pressing normally against a surface of the fiber preform constituting the bottom platform of the vane, and
fifth and sixth compacting blocks having surfaces for pressing normally against respective surfaces of the fiber preform constituting upstream and downstream flanges of bottom platform of the vane.

5. The method according to claim 4 , wherein the closure blocks include
a first closure block having a first surface for pressing normally against a surface of the third compacting block, and a second surface, remote from the first surface, for pressing against the surface of the fiber preform constituting the top platform of the vane,
a second closure block having a first surface for pressing normally against a surface of the fourth compacting block, and a second surface, remote from the first surface, for pressing against the surface of the fiber preform constituting the bottom platform of the vane,
a third closure block having a first surface for pressing normally against a surface of the fifth compacting block, and a second surface, remote from the first surface, for pressing against the surface of the fiber preform constituting the upstream flange of the bottom platform of the vane, and
a fourth closure block having a first surface for pressing normally against a surface of the sixth compacting blocks, and a second surface, remote from the first surface, for pressing against the surface of the fiber preform constituting the downstream flange of the bottom platform of the vane.

Assignees

• Safran Aircraft Engines

Inventors

• Plante Romain
• Lacroix Lise
• Patrigeon Olivier
• Cauchois Jean-Pierre
• Burek Pascal

Classifications

• B29D99/0025

  Producing blades or the like, e.g. blades for turbines, propellers, or wings · CPC title

• B29C70/48 Primary

  and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM] {, e.g. by vacuum} · CPC title

• B29C45/0005 Primary

  using fibre reinforcements · CPC title

• B29C70/461 Primary

  Rigid movable compressing mould parts acting independently from opening or closing action of the main mould · CPC title