Fan rotor and associated turbojet engine

Patent metadata

Field	Value
Publication number	US-9540935-B2
Application number	US-201213983241-A
Country	US
Kind code	B2
Filing date	Feb 20, 2012
Priority date	Feb 21, 2011
Publication date	Jan 10, 2017
Grant date	Jan 10, 2017

Abstract

A fan rotor including a disk carrying blades including roots engaged in slots in the disk, a frustoconical cap mounted on the disk upstream from the blades, and a retaining mechanism axially retaining the blades on the disk and including a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk, and a mechanism preventing the ring from moving in rotation, which includes an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk.

First claim

The invention claimed is:

1. A fan rotor comprising:
a disk carrying blades including roots engaged in substantially axial slots in an outer periphery of the disk;
a substantially frustoconical cap mounted on the disk upstream from the blades;
retaining means for axially retaining the blades on the disk and comprising a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk; and
means for preventing the ring from moving in rotation, which means comprises an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk;
wherein the annulus includes lugs extending radially inwards and including holes passing axial bolts for fastening the annulus on the disk, the cap being fastened on the disk by axial bolts passing through the holes in some of the lugs of the annulus, and
further comprising an indexing peg mounted in aligned holes in the annulus and in the disk and including an upstream head received in a blind hole in an inner radial bead of the cap.

2. A fan rotor according to claim 1 , wherein, in its middle portion, the cap includes an inner annular bead including both blind axial holes formed therein that open out downstream and that serve as housings for heads of the bolts for fastening the annulus on the disk, and through axial holes for passing bolts for fastening the cap on the disk.

3. A fan rotor according to claim 2 , wherein the inner radial bead of the cap includes two through axial holes that are tapped for passing extractor screws.

4. A fan rotor according to claim 1 , wherein the cap is made of light metal, or of aluminum, and the annulus is made of metal that withstands being torn away, or high alloy steel.

5. A turbojet, comprising a fan rotor according to claim 1 .

Assignees

• Perdrigeon Christophe
• Jablonski Laurent
• Joly Philippe Gerard Edmond
• Snecma

Inventors

• Perdrigeon Christophe
• Jablonski Laurent
• Joly Philippe Gerard Edmond

Classifications

• F04D29/321 Primary

  for axial flow compressors · CPC title

• F01D5/3069 Primary

  between two discs or rings · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D29/322

  Blade mountings · CPC title

• F01D5/3015

  with side plates · CPC title