Method of making a metal reinforcing member for a blade of a turbine engine

Patent metadata

Field	Value
Publication number	US-9874103-B2
Application number	US-201314402182-A
Country	US
Kind code	B2
Filing date	May 31, 2013
Priority date	Jun 1, 2012
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

Abstract

A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.

First claim

The invention claimed is:

1. A method of making a metal reinforcing member for mounting on a leading edge or a trailing edge of a composite blade of a turbine engine, the method comprising:
shaping two metal sheets to approximate a final shape of the reinforcing member that is to be made;
positioning the two sheets on either side of a core reproducing inside shapes of a suction side and of a pressure side of the reinforcing member and including at least one recess for forming a mold for a spacer for positioning the reinforcing member relative to the leading edge or the trailing edge of the blade;
assembling the two sheets together around the core in a leaktight manner and in a vacuum;
conforming the sheets onto the core by hot isostatic compression; and
cutting the sheets to separate the reinforcing member and release the core.

2. A method according to claim 1 , wherein the sheets are made of titanium-based alloy.

3. A method according to claim 1 , wherein the mold of the positioning spacer presents a draft angle for facilitating separation of the reinforcing member from the core.

4. A single-piece metal reinforcing member made by the method of claim 1 , for mounting on a leading edge or a trailing edge of a composite blade for a turbine engine, the reinforcing member comprising:
a first wall for applying against a pressure side surface of the blade and a second wall for applying against a suction side surface of the blade,
the first and second walls defining a cavity having a bottom that includes a spacer projecting into the cavity and made integrally with the reinforcing member,
the spacer being for pressing against the leading edge or the trailing edge of the blade.

5. A single-piece metal reinforcing member for mounting on a leading edge or a trailing edge of a composite blade for a turbine engine, the reinforcing member comprising:
a first wall for applying against a pressure side surface of the blade and a second wall for applying against a suction side surface of the blade,
the first and second walls defining a cavity having a bottom that includes a spacer projecting into the cavity, a first end of the spacer being made integrally with the reinforcing member,
the spacer being for pressing against the leading edge or the trailing edge of the blade,
wherein said spacer has a second planar end projecting into said cavity and being free of contact with the first and second walls, and
wherein the first wall, the second wall, and the spacer are diffusion welded to each other.

6. A metal reinforcing member according to claim 5 , comprising at least two spacers that are spaced apart from each other, each spacer having a second planar end projecting into said cavity and being free of contact with the first and second walls.

7. A metal reinforcing member according to claim 6 , wherein each of the two spacers is situated in proximity of one of longitudinal ends of the reinforcing member.

8. A blade for a turbine engine or an airplane turboprop or turbojet, the blade comprising:
an airfoil of composite material including a pressure side surface and a suction side surface that are connected together by a trailing edge and by a leading edge;
at least one reinforcing member according to claim 5 , having its first and second walls adhesively bonded to the pressure side and suction side surfaces of the airfoil;
the spacer coming to bear against the leading edge or the trailing edge of the blade.

9. A turbine engine blade according to claim 8 , wherein the leading edge or the trailing edge of the blade on which the reinforcing member is fastened includes at least one chamfered zone, each spacer including a plane end surface that comes to bear against the leading edge or the trailing edge in the corresponding chamfered zone.

10. A turbine engine blade according to claim 8 , wherein the spacer extends along a straight or curved generator line corresponding to a straight or curved profile of the leading edge or the trailing edge in the zone where the spacer bears against the edge.

Assignees

• Snecma

Inventors

• Leconte Gilbert Michel Marin
• Klein Gilles Charles Casimir
• Franchet Jean-Michel Patrick Maurice
• Magnaudeix Dominique

Classifications

• B21D26/053

  characterised by the material of the blanks · CPC title

• B23K2201/001

  Operations & Transport · mapped topic

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• B23P15/04

  turbine or like blades from several pieces · CPC title