Propeller ring made of composite material for a turbomachine

Patent metadata

Field	Value
Publication number	US-2016123162-A1
Application number	US-201514927672-A
Country	US
Kind code	A1
Filing date	Oct 30, 2015
Priority date	Oct 31, 2014
Publication date	May 5, 2016
Grant date	—

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

1 . A propeller ring of a turbomachine comprising 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 propeller ring wherein the annular body is made of a composite material comprising a fibrous reinforcement densified by a polymer matrix and further comprises a plurality of metallic inserts each configured to receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body.

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

3 . The propeller ring according to claim 1 , wherein the metallic insert is cylinder of revolution or conical.

4 . The propeller ring according to claim 3 , wherein the metallic insert is cylinder of revolution and further comprises an annular protuberance, said annular protuberance being embedded in the composite material.

5 . The propeller ring according to claim 4 , wherein each housing comprises a radially outer part configured to receive a root of a blade and a radially inner part, opposite the radially outer part, the annular protuberance extending near the radially outer part.

6 . The propeller ring according to claim 1 , wherein the metallic insert has a cross-section substantially elongated in a tangential direction of the propeller ring.

7 . The propeller ring according to claim 1 , wherein the fibrous reinforcement comprises fibres of carbon, glass, aramid or ceramic, the matrix comprises a polymer of epoxide, bismaleimide or polyimide type and the insert is made of titanium.

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

9 . A propeller comprising a propeller ring according to claim 1 and blades, housed in the radial housings of the propeller ring.

10 . A turbomachine having blades with variable pitch, comprising a propeller ring according to claim 1 .

11 . The turbomachine according to claim 10 , wherein the propeller is unducted.

Assignees

• Snecma

Inventors

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

Classifications

• F01D5/3023

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

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2240/50

  Bearings · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F01D7/00 Primary

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title