Vane with sealed lattice in a shroud of an axial turbomachine compressor

Patent metadata

Field	Value
Publication number	US-9957980-B2
Application number	US-201514808256-A
Country	US
Kind code	B2
Filing date	Jul 24, 2015
Priority date	Jul 25, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.

First claim

I claim:

1. An axial turbomachine stator, comprising:
an annular wall with a guiding surface for guiding an annular flow of the turbomachine;
a circular row of stator vanes, at least one of the stator vanes comprising:
an airfoil which is intended to extend radially in the flow from the guiding surface; and
a securing portion which extends from the guiding surface radially opposite the airfoil, and which is secured to the wall;
wherein the securing portion of the vane comprises:
a lattice secured to the wall within the wall's radial thickness in order to fix the vane to the wall via the lattice

wherein the lattice is a three-dimensional lattice with interconnected rods which are joined to each other so as to form meshes, the lattice comprising:
a plurality of meshes over the thickness and over the length of the airfoil and in the radial direction.

2. The axial turbomachine stator in accordance with claim 1 , wherein the at least one vane comprises:
a leading edge, a trailing edge, an intrados surface, and an extrados surface, the intrados surface and the extrados surface extending from the leading edge to the trailing edge, and the lattice extending at least from the leading edge to the trailing edge, and from the intrados surface to the extrados surface of the airfoil.

3. The axial turbomachine stator in accordance with claim 1 , wherein the wall comprises:
a sealing joint layer, the lattice being at least partially secured in the radial thickness of the sealing joint layer.

4. The axial turbomachine stator in accordance with claim 1 , wherein the wall comprises:
at least one opening in which the securing portion is fixed, the lattice extending radially beyond the opening.

5. The axial turbomachine stator in accordance with claim 1 , wherein the wall is formed by an annular array of angular segments to which the lattice is secured.

6. The axial turbomachine stator in accordance with claim 1 , wherein the guiding surface is radially at a height between the airfoil and the securing portion, the lattice forming the vane's radial end.

7. The axial turbomachine stator in accordance with claim 1 , wherein the wall is integral with and is formed by a material which fills the lattice.

8. The axial turbomachine stator in accordance with claim 1 , wherein the lattice extends over the majority of the axial length of the wall and over the majority of the radial thickness of the wall.

9. The axial turbomachine stator in accordance with claim 1 , wherein the airfoil comprises:
a solid body which extends over the majority of the radial height thereof, the lattice being broader in the circumferential direction than said airfoil.

10. The axial turbomachine stator in accordance with claim 1 , wherein the lattice comprises:
a compactness which is less than one of the group consisting:
60%;
30%; and
10%.

11. The axial turbomachine stator in accordance with claim 1 , wherein the securing portion is a first securing portion, and the lattice is a first lattice, the wall is a first wall, the stator further comprising:
a second wall which is concentric with the first wall, the at least one vane further comprising:
a second securing portion with a second lattice which is radially opposite the first lattice relative to the airfoil and which is secured in the second wall.

12. The axial turbomachine stator in accordance with claim 1 , wherein the airfoil and the lattice are integral and are produced by means of additive manufacturing.

13. An axial flow turbine engine compressor, comprising:
an annular vein guiding an axial annular flow; and
a stator comprising:
an annular wail comprising:
an annular guiding surface guiding said axial annular flow; and
a circular row of stator vanes, at least one of the stator vanes comprising:
an airfoil extending radially through the axial annular flow from the guiding surface; and
a securing portion, the airfoil and the securing portion being radially stacked;
wherein the securing portion of the vane comprises:
 a lattice which is secured to the wall in order to fix the vane to the wall via the lattice, the guiding surface being radially placed between the lattice and the airfoil of said vane,

wherein the lattice is a three-dimensional lattice with interconnected rods which are joined to each other so as to form meshes, the lattice comprising a plurality of meshes over the thickness and over the length of the airfoil and in the radial direction,
wherein the stator comprises:
a layer of abradable material for cooperating by abrasion with the rotor of the compressor, the lattice being at least partially arranged in the radial thickness of the layer of abradable material, and said layer filling the lattice.

14. The axial flow turbine engine compressor in accordance with claim 13 , wherein the airfoil comprises:
a fixing platform with a fixing shaft which is arranged radially opposite the lattice relative to the airfoil, the compressor further comprising:
an outer housing, the platform being fixed to the outer housing by means of the fixing shaft.

15. The axial flow turbine engine compressor in accordance with claim 13 , wherein the wall is an inner shroud which is produced from a composite material having an organic matrix.

16. The axial flow turbine engine compressor in accordance with claim 13 , wherein the wall comprises:
an upstream axial half and a downstream axial half, the lattice being axially spaced apart from one of the axial halves, the wall forming the inlet of the compressor.

17. An axial flow turbomachine, comprising:
an annular primary vein guiding a primary flow;
an annular secondary vein guiding a secondary flow, the secondary vein being around the primary vein;
an inner shroud embraced by the primary flow; and
several annular rows of stator vanes, at least one of the stator vanes comprising:
an airfoil extending radially from the inner shroud through the primary flow; and
a securing portion placed inside the inner shroud, the securing portion of the vane comprising:
a lattice which is secured inside the inner shroud in order to fix the vane to the wall via the lattice,

wherein the lattice is a three-dimensional lattice with interconnected rods which are joined to each other so as to form meshes, the lattice comprising a plurality of meshes over the thickness and over the length of the airfoil and in the radial direction,
wherein the airfoil comprises:
a solid body which extends over the majority of the radial height thereof,
the lattice being broader in the circumferential direction than said airfoil.

Assignees

• Techspace Aero Sa
• Safran Aero Boosters Sa

Inventors

• Englebert Eric

Classifications

• F04D29/083

  especially adapted for elastic fluid pumps · CPC title

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F04D19/022

  with concentric rows of vanes; · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title