Secondary flow guide vane of a turbomachine and turbomachine provided therewith

Patent metadata

Field	Value
Publication number	US-12372001-B2
Application number	US-202318730612-A
Country	US
Kind code	B2
Filing date	Jan 18, 2023
Priority date	Jan 21, 2022
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

The invention relates to a secondary flow stator vane ( 1 ) for a turbomachine, comprising skins ( 2, 3 ) having end portions ( 21, 31 ) delimiting an opening ( 5 ) and a cavity ( 4 ) therebetween, which skins diverge from one another in a direction (Y). A filler material ( 41 ) is located in the cavity ( 4 ) at a distance from the opening ( 5 ). A reinforcement ( 6 ), the density of which is higher than the density of the material ( 41 ), comprises a first reinforcement portion ( 61 ) located in the cavity ( 4 ) against the material ( 41 ) and a second reinforcement portion ( 62 ) for closing the opening ( 5 ) between the portions ( 21, 31 ) to form a single piece.

First claim

The invention claimed is:

1. A secondary flow guide vane of a turbomachine, comprising a first outer skin and a second outer skin, which are made of a first composite material and which are connected to one another,
the first outer skin comprising a first end part, the second outer skin comprising a second end part distant from the first end part,
the first end part and the second end part being located on the same mounting side of the vane, delimiting between them an opening and branching away from one another along a thickness direction,
wherein
the vane further comprises:
a cavity, which is located along the thickness direction between the first outer skin and the second outer skin and which opens into the opening,
a filling material which has a first density and which is located in the cavity and at a non-zero distance from the opening,
a reinforcement, which has a second density greater than the first density and which comprises a first reinforcing part located in the cavity and against the filling material and a second reinforcing part, which closes the opening between the first end part and the second end part,
the first reinforcing part forming a single piece with the second reinforcing part.

2. The guide vane as claimed in claim 1 , wherein the first reinforcing part comprises a contact surface for contact with the filling material in the cavity,
the first outer skin and the second outer skin having a leading edge and a trailing edge, distant from one another along a width direction of the vane, which is transverse with respect to the thickness direction,
the mounting side of the vane being located under an airflow line along a height direction of the vane, transverse with respect to the thickness direction and with respect to the width direction,
the airflow line forming a limit of the secondary flow of the turbomachine on the first outer skin and on the second outer skin,
a first upstream part of the contact surface, which is located on the side of the leading edge, is located along the height direction above a second upstream part of the airflow line, which is located on the side of the leading edge.

3. The guide vane as claimed in claim 2 , wherein a first downstream part of the contact surface, which is located on the side of the trailing edge, is located along the height direction below a second downstream part of the airflow line, which is located on the side of the trailing edge.

4. The guide vane as claimed in claim 2 , wherein the first upstream part of the contact surface is located along the height direction at a height greater than or equal to 50 mm and less than or equal to 100 mm above the opening.

5. The guide vane as claimed in claim 2 , wherein the first upstream part of the contact surface is located along the height direction at a height greater than or equal to 50 mm and less than or equal to 100 mm above the second upstream part of the airflow line.

6. The guide vane as claimed in claim 1 , wherein a plate makes a connection between the first end part and the second end part, is attached under and against the first end part and the second end part and is located against the opening and against the second reinforcing part.

7. The guide vane as claimed in claim 1 , wherein the second reinforcing part extends as a base of non-zero height under the first end part, under the second end part and under the opening.

8. The guide vane as claimed in claim 7 , wherein a plate is attached under and against the base.

9. The guide vane as claimed in claim 6 , wherein the plate is made of a composite material.

10. The guide vane as claimed in claim 1 , wherein the reinforcement is made of the first composite material.

11. The guide vane as claimed in claim 1 , wherein the reinforcement is made of a second non-woven composite material with fibers embedded in a matrix.

12. The guide vane as claimed in claim 1 , wherein the reinforcement is made of at least one metal.

13. The guide vane as claimed in claim 1 , wherein the reinforcement has a Young modulus greater than or equal to 5 GPa.

14. The guide vane as claimed in claim 2 , wherein the filling material comprises at the contact surface a protruding part, which fits into a hollow part of the first reinforcing part.

15. A aeronautical turbomachine with no fairing, comprising:
a casing,
a fan having a fan hub and peripheral fan blades, secured to the fan hub,
the fan hub having a downstream hub part, which is surrounded by an inner surface of an upstream part of the casing and which protrudes from the upstream part of the casing,
the fan hub being mounted rotatably with respect to the upstream part of the casing about an axis of rotation, directed from upstream to downstream,

the turbomachine further comprising secondary flow guide vanes as claimed in claim 1 , which are located, by their mounting side, adjacent to an outer wall of the upstream part of the casing and are located downstream with respect to the peripheral fan blades.

Assignees

• Safran Aircraft Engines

Inventors

• Bazot Olivier
• Joudon Vincent

Classifications

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F03B3/126

  Rotors for essentially axial flow, e.g. for propeller turbines (with adjustable blades F03B3/14) · CPC title

• F04D29/305

  Flexible vanes · CPC title