Stiffened hub for unshrouded propeller

Patent metadata

Field	Value
Publication number	US-10501168-B2
Application number	US-201515312381-A
Country	US
Kind code	B2
Filing date	May 7, 2015
Priority date	May 21, 2014
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

The invention relates to a hub for an unducted propeller ( 14 ) having variable-pitch blades ( 18 ) of a turbine engine, comprising two parallel annular side walls ( 34 ) between which are arranged rings ( 36 ) which are distributed angularly in a regular manner around a longitudinal axis (A) of the hub, which are connected to the annular side walls ( 34 ), and which comprise compartments ( 26 ) receiving bearings ( 32 ) having radial axes (R) for guiding in rotation roots ( 30 ) of blades of said propeller, said rings ( 36 ) being connected in pairs by connection means ( 40 ) which are arranged between the annular side walls ( 34 ) and which comprise substantially radial reinforcing partitions ( 42, 44, 46 ), characterised in that at least some of said reinforcing partitions ( 42, 44, 46 ) are connected to said annular side walls ( 34 ).

First claim

The invention claimed is:

1. The hub for an unducted propeller having variable-pitch blades of a turbine engine, comprising two parallel annular side walls between which are arranged rings which are distributed angularly in a regular manner around a longitudinal axis of the hub, which are connected to the annular side walls, and which comprise compartments which are designed to receive bearings having radial axes for guiding in rotation roots of blades of said propeller, said rings being connected in pairs by connection means which are arranged between the annular side walls and which comprise reinforcing partitions which are substantially radial with respect to the longitudinal axis of the hub, wherein at least some of said reinforcing partitions are connected to said annular side walls.

2. A hub according to claim 1 , wherein the connection means comprise first reinforcing partitions bordering the side walls, and/or second reinforcing partitions bordering the rings, and/or third reinforcing partitions which define recesses between the rings.

3. A hub according to claim 2 , wherein the connection means of two adjacent rings of the rings define a central recess and four peripheral recesses which are regularly distributed around the central recess.

4. A hub according to claim 3 , wherein the central recess has a circular cross section and wherein each peripheral recess has a substantially trapezoidal cross section.

5. A hub according to claim 3 , wherein the central recess has a cross section in the shape of a hexagon and in that each peripheral recess has a substantially triangular cross section.

6. A hub according to claim 2 , wherein the connection means of two adjacent rings of the rings comprise at least two third partitions which cross each other and which define four main recesses.

7. A hub according to claim 6 , wherein the third partitions are oriented either in the transverse and longitudinal directions or diagonally.

8. A hub according to claim 2 , wherein the connection means of two adjacent rings of the rings comprise at least first partitions bordering the side walls, and at least second partitions bordering the rings.

9. A turbine engine, comprising at least one hub according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

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

Classifications

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• F04D29/326

  comprising a rotating shroud · CPC title

• F01D7/00

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

• Y02T50/66

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title