Lattice type blade of an axial turbine engine compressor

Patent metadata

Field	Value
Publication number	US-10400625-B2
Application number	US-201514919104-A
Country	US
Kind code	B2
Filing date	Oct 21, 2015
Priority date	Oct 28, 2014
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

The invention relates to a blade of a low-pressure compressor of an axial turbine engine. The blade comprises a vane in which a cavity is formed. The vane has a leading edge and a trailing edge, an intrados surface and an extrados surface which extend from the leading edge to the trailing edge, an outer casing which forms the intrados surface and the extrados surface and which delimits the cavity. The blade further comprises closed foam, such as a polymethacrylic foam, which blocks the cavity in order to isolate it from the environment of the blade. The blade further has a three-dimensional lattice which is formed in the cavity and which is integral with the vane of the blade. This barrier protects from chemical attacks and the introduction of impurities. The invention also relates to a production method for a hollow turbine engine blade which is filled with foam.

First claim

What is claimed is:

1. A blade of an axial turbine engine, the blade comprising:
a vane which is intended to project radially in a flow of the turbine engine;
a cavity which is formed in of the vane of the blade;
a reinforcing lattice within the cavity; and
a closed foam in contact with the reinforcing lattice and closing the cavity in order to isolate the cavity from the exterior of the blade, the reinforcing lattice being polyhedral meshes delimited by rods arranged in at least three directions and the lattice forming a plurality of meshes in accordance with the thickness of the vane, wherein the blade comprises a radial end with a fixing portion, the cavity comprising an opening in the radial end, and the fixing portion comprising two fixing lugs which are axially opposed, wherein the opening is filled with the closed foam and is axially between the two fixing lugs, and wherein at least one of the two fixing lugs has a cell being connected with the cavity, wherein the reinforcing lattice extends in the cell and the cell is filled with the closed foam.

2. The blade in accordance with claim 1 , wherein the closed foam is polymer foam.

3. The blade in accordance with claim 1 , wherein the cavity has a volume and the foam is present in more than half of the volume of the cavity.

4. The blade in accordance with claim 1 , wherein, the opening forms a waist between the cavity and the exterior of the blade, the closed foam tightly closing the opening.

5. The blade in accordance with claim 1 , wherein the lattice comprises rods that are distributed in the cavity and that have rod junction nodes.

6. The blade in accordance with claim 1 , wherein the cavity has a volume and the lattice extends in more than half of the volume of the cavity.

7. The blade in accordance with claim 1 , wherein the blade comprises a leading edge, a trailing edge, an intrados surface and an extrados surface that extend from the leading edge to the trailing edge, an outer shell which forms the intrados surface and the extrados surface and that delimits the cavity.

8. The blade in accordance with claim 7 , wherein the shell has a constant thickness over the entirety of the intrados and the extrados surfaces, the shell being tight over the entire surface of the intrados and the extrados.

9. The blade in accordance with claim 7 , wherein the vane has a radial height and the thicknesses of the shell are constant over the radial height of the vane.

10. The blade in accordance with claim 1 , wherein the foam has pores that occupy more than 50% of the foam, and wherein the density of the foam is less than 200 kg/m3.

11. A production method for a blade of an axial turbine engine, the method comprising:
production of a blade with a vane that is intended to extend radially in a flow of the turbine engine; and a cavity that is formed in the vane of the blade, wherein the production of the blade comprises producing the blade by additive manufacturing by depositing powder layers, wherein the production of the blade comprises simultaneously forming a reinforcing lattice inside the cavity and the vane of the blade, wherein, at a radial end of the vane, the blade comprises a fixing portion comprising two fixing lugs, wherein at least one of the two fixing lugs has a cell being connected with the cavity, wherein the reinforcing lattice extends in the cell;
filling of the cavity through an opening of the vane with a closed foam in order to at least partially occupy a free space of the cavity and the cell, the opening being formed
at the radial end with the fixing portion and arranged axially between the two fixing lugs, the cavity being opened through the radial end.

12. The production method in accordance with claim 11 , wherein filling the cavity and the cell comprises one of:
pouring a precursor material of the closed foam onto the lattice; and
injecting the precursor into the cavity and the cell.

13. The production method in accordance with claim 11 , wherein, at the end of filling the cavity and the cell with the closed foam, the cavity and the cell are completely occupied by the foam.

Assignees

• Techspace Aero Sa
• Safran Aero Boosters Sa

Inventors

• Cortequisse Jean-Francois

Classifications

• F01D25/06 Primary

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title

• B22F10/20 Primary

  Direct sintering or melting · CPC title

• F05D2300/612

  Foam · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title