Guide vane for a turbomachine fan

Patent metadata

Field	Value
Publication number	US-11149566-B2
Application number	US-201816955449-A
Country	US
Kind code	B2
Filing date	Dec 17, 2018
Priority date	Dec 21, 2017
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A guide vane in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis of the vane so that the differential thermal expansions compensate for the bending deformations caused by the aerodynamic forces exerted on the outer vane surface.

First claim

The invention claimed is:

1. A guide vane for a turbomachine fan, comprising two opposite ends intended to be mounted on an internal casing and an external casing, concentric with the internal casing, of the turbomachine, the vane being hollow and traversed by a main heat transfer fluid circulation conduit extending, from a fluid inlet at a first of the vane ends, into at least a height portion of the vane, the vane being composed of sections, each at a uniform position in a radial direction of the turbomachine, the sections being each composed of a central region and at least one end region on either side of a principal axis of flexural inertia of the section, the end region including a leading edge and a trailing edge of the vane, wherein, in each vane section of the height portion of the vane, the main conduit extends merely in the central region, said principal axis of flexural inertia being an axis about which the section has a quadratic moment of inertia and the vane has the lowest flexural rigidity.

2. The guide vane according to claim 1 , wherein the vane is also traversed, in the height portion of the vane, by lateral fluid circulation conduits between the main conduit and, respectively, the leading edge and the trailing edge of the vane, the lateral conduits extending between a fluid outlet and a first coupling, joining the ends of the lateral conduits to an end of the main conduit.

3. The guide vane according to claim 2 , wherein the lateral conduits extend, in each section of the height portion of the vane, into said end region.

4. A guide section for a turbomachine fan, comprising a stage composed of vanes according to claim 1 .

5. The guide section for a turbomachine fan, comprising a stage composed of vanes according to claim 2 .

6. The guide section according to claim 5 , comprising an oil circulation direction inversion arrangement either in the main conduit, or in the lateral conduits.

7. A turbomachine, comprising a secondary stream and at least one guide vane according to claim 1 .

8. A turbomachine, comprising a fan and the guide section according to claim 5 , immediately downstream from the fan.

Assignees

• Safran Aircraft Engines

Inventors

• Bordoni Nils Edouard Romain

Classifications

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title