Outlet guide vane for aircraft turbomachine, with improved lubricant cooling function

Patent metadata

Field	Value
Publication number	US-10697312-B2
Application number	US-201815914150-A
Country	US
Kind code	B2
Filing date	Mar 7, 2018
Priority date	Mar 13, 2017
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

First claim

The invention claimed is:

1. A guide vane configured to be positioned in all or some of an air flow in a twin-spool aircraft turbomachine fan, the guide vane comprising:
a root, a tip and, an aerodynamic flow straightening part located between the root and the tip of the guide vane, said aerodynamic flow straightening part of the guide vane comprising a first internal lubricant cooling passage extending along a first main lubricant flow direction from the root towards the tip of the guide vane, said first internal lubricant cooling passage being partly limited by an intrados wall and an extrados wall of the guide vane,
wherein the aerodynamic flow straightening part of the guide vane is made in a single piece and also comprises heat transfer fins arranged in the first passage, each of the fins including a first end in direct contact with the intrados wall and a second end in direct contact with the extrados wall to connect the intrados and extrados walls, each of the fins extending approximately parallel to the first main lubricant flow direction, said fins being distributed in successive rows of fins following each other along the first main lubricant flow direction and made such that for a first row and a second row of staggered directly consecutive fins, the first row comprising at least several fins forming a positive acute angle A 1 with a dummy reference plane of the guide vane parallel to the first main lubricant flow direction, while the second row comprises at least several fins forming a negative acute angle A 2 with said dummy reference plane, the first row of fins and the second row of fins alternate in the first main lubricant flow direction.

2. The guide vane according to claim 1 , wherein the positive acute angle A 1 and the negative acute angle A 2 are between 30 and 60°.

3. The guide vane according to claim 1 , wherein for the first row and the second row of directly consecutive staggered fins, all fins in the first row form the positive acute angle A 1 with the dummy reference plane, while all fins in the second row form the negative acute angle A 2 with said dummy reference plane.

4. The guide vane according to claim 3 , wherein the positive acute angle A 1 is identical for all fins in the first row, while the negative acute angle A 2 is identical for all fins in the second row.

5. The guide vane according to claim 3 , wherein the fins in the first row are at a uniform spacing from each other along a transverse direction of the guide vane from a leading edge towards a trailing edge of the aerodynamic flow straightening part, the fins in the second row are at a uniform spacing from each other along the transverse direction, and when viewed along the first main lubricant flow direction, the fins in the first row are arranged between the fins of the second row, so as to jointly form a broken line.

6. The guide vane according to claim 1 , wherein, for the first row and the second row of directly consecutive staggered fins, each of these rows comprises fins in alternation along a transverse direction of the guide vane from a leading edge towards a trailing edge of the aerodynamic flow straightening part, with each fin forming the positive acute angle A 1 with the dummy reference plane and with each fin forming the negative acute angle A 2 with said dummy reference plane.

7. The guide vane according to claim 6 , wherein, when viewed along the first main lubricant flow direction, the fins in the first row jointly form a first broken line and the fins in the second row jointly form a second broken line, the first and the second broken lines being offset from each other along the transverse direction such that at least some of the fins in the first row cross at least some of the fins in the second row.

8. The guide vane according to claim 6 , wherein the first broken line and the second broken line are periodic with the same period T, and they are offset from each other along the transverse direction by a value equal to T/n, where n is a positive integer number preferably between two and four.

9. The guide vane according to claim 1 , wherein the aerodynamic flow straightening part made in a single piece also includes heat transfer fins made in a second internal lubricant cooling passage extending along a second principal lubricant flow direction from the tip towards the root of the guide vane, in which there is a fluid connection between said second internal lubricant cooling passage and the first internal lubricant cooling passage through a bend in which there are no heat transfer fins.

10. A turbomachine for an aircraft, comprising:
a plurality of guide vanes according to claim 1 , located downstream or upstream from the twin-spool aircraft turbomachine fan of the turbomachino.

11. A method of fabrication of the guide vane according to claim 1 , wherein said aerodynamic flow straightening part of the guide vane is made in a single piece by additive fabrication, with the dummy reference plane of the guide vane being located parallel to a vane support surface during fabrication.

12. The guide vane according to claim 1 , wherein the aerodynamic flow straightening part made in a single piece also includes a second internal lubricant cooling passage extending along a second principal lubricant flow direction from the tip towards the root of the guide vane, the second principal lubricant flow direction being parallel to the first principal lubricant flow direction.

13. The guide vane according to claim 12 , further comprising a bend that provides a fluid connection between said second internal lubricant cooling passage and the first internal lubricant cooling passage.

14. The guide vane according to claim 12 , wherein said second internal lubricant cooling passage is adjacent to a leading edge of the guide vane and the first internal lubricant cooling passage is adjacent to a trailing edge of the guide vane.

15. The guide vane according to claim 9 , wherein said second internal lubricant cooling passage is adjacent to a leading edge of the guide vane and the first internal lubricant cooling passage is adjacent to a trailing edge of the guide vane.

Assignees

• Safran Aircraft Engines

Inventors

• Boutaleb Mohamed-Lamine
• Caty Fabien Roger Gaston
• Dreano Sebastien Vincent Francois
• Papin Thierry Georges Paul
• Perdrigeon Christophe Marcel Lucien
• Zaccardi Cedric

Classifications

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F28D1/0233

  with air flow channels · CPC title

• F01D5/188

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F28D2021/0049

  for lubricants, e.g. oil coolers · CPC title

• F28F2250/02

  Streamline-shaped elements · CPC title