Propeller ring made of composite material for a turbomachine

Patent metadata

Field	Value
Publication number	US-10378368-B2
Application number	US-201514927672-A
Country	US
Kind code	B2
Filing date	Oct 30, 2015
Priority date	Oct 31, 2014
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

A propeller ring of a turbomachine including an annular body substantially coaxial to a principal axis and a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade, the annular body being made of composite material including a fibrous reinforcement densified by a polymer matrix and further including a plurality of metallic inserts configured to each receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body.

First claim

The invention claimed is:

1. A propeller ring of a turbomachine comprising:
an annular body coaxial to a principal axis and made of a composite material including a fibrous reinforcement densified by a polymer matrix;
a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade of variable pitch; and
a plurality of metallic inserts each configured to receive the root of the blade of variable pitch, the plurality of metallic inserts being anchored in the composite material of the annular body and including an annular protuberance embedded in the composite material of the annular body, wherein at least one of the plurality of metallic inserts is a cylinder of revolution or conical, and has a geometry enabling the metallic inserts to be attached directly to the annular body and to be held inside the annular body by contact pressure.

2. The propeller ring according to claim 1 , wherein fibres of the fibrous reinforcement of the composite material have an orientation parallel to a tangential direction of the propeller ring.

3. The propeller ring according to claim 1 , wherein each of the plurality of radial housings includes a radially outer part configured to receive the root of the blade of variable pitch and a radially inner part, opposite the radially outer part, the annular protuberance extending near the radially outer part.

4. The propeller ring according to claim 1 , wherein the at least one of the plurality of metallic inserts has a cross-section substantially elongated in a tangential direction of the propeller ring.

5. The propeller ring according to claim 1 , wherein
the fibrous reinforcement includes fibres of carbon, glass, aramid or ceramic,
the polymer matrix includes a polymer of epoxide, bismaleimide or polyimide type, and
the at least one of the plurality of metallic inserts is made of titanium.

6. The propeller ring according to claim 1 , wherein
the annular body has a polygonal shape.

7. A propeller comprising:
the propeller ring according to claim 1 ; and
each blade of variable pitch housed in the radial housings of the propeller ring.

8. A turbomachine comprising:
the propeller ring according to claim 1 .

9. The turbomachine according to claim 8 , wherein the propeller is unducted.

10. The propeller ring according to claim 1 , wherein each of the radial housings further receives a bearing configured to adjust an angular orientation of the blade.

11. The propeller ring according to claim 1 , wherein a thickness of the annular protuberance gradually decreases between a radially outer part of the at least one of the plurality of metallic inserts and a radially inner part of the annular body extending away from the radially outer part of the at least one of the plurality of metallic inserts.

12. A propeller ring of a turbomachine comprising:
an annular body coaxial to a principal axis and made of a composite material including a fibrous reinforcement densified by a polymer matrix, the annular body including a plurality of radial housings and a plurality of metallic inserts, wherein
the plurality of radial housings is uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade of variable pitch, and
each of the plurality of metallic inserts including an annular protuberance embedded in the composite material of the annular body is configured to receive the root of the blade of variable pitch and anchored in the composite material of the annular body and, wherein at least one of the plurality of metallic inserts is a cylinder of revolution or conical, and has a geometry enabling the metallic inserts to be attached directly to the annular body and to be held inside the annular body by contact pressure, wherein a thickness of the annular protuberance at a radially outer part of the at least one of the plurality of metallic inserts is greater than the thickness at a radially inner part of the annular body, opposite the radially outer part of the at least one of the plurality of metallic inserts.

13. The propeller ring according to claim 12 , wherein the annular protuberance includes a conical cross-section, wherein a wider part of the annular protuberance extends beyond a radially outer surface of the annular body.

14. The propeller ring according to claim 12 , wherein the annular protuberance forms an anti-tear member configured to distribute centrifugal forces to the annular body.

15. The propeller ring according to claim 12 , wherein a geometry of the annular body is such that a thickness of material extending about the at least one of the plurality of metallic inserts is continuous and constant.

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Tajan Sebastien Emile Philippe
• Derrez Charles-Henri Michel Marie
• Lafitte Anthony
• Le Pecheur Cyril Roger Yves

Classifications

• F05D2240/50

  Bearings · CPC title

• F05D2240/20

  Rotors · CPC title

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• F01D5/3023

  of radial insertion type, e.g. in individual recesses · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title