# US 9,518,470 B2 · Device for attaching blades to a turbine engine rotor disk

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- Number: US 9,518,470 B2
- Document ID: US9518470B2
- Status: Granted
- Kind: B2
- Application number: 13/892,601
- Filed: 2013-05-13
- Published: 2013-11-14
- Granted: 2016-12-13
- Earliest claimed: 2012-05-14
- Assignees: Snecma; Herakles
- Applicants: Snecma; Herakles
- Inventors: Hubert Illand; Didier Fabre; Amaury Roussely-Rousseau
- Web page: https://patentgrep.com/patent/US9518470B2

## CPC

- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/3007: {of axial insertion type}
- F01D 5/3053: {by means of pins}
- F05D 2230/90: Coating; Surface treatment
- F05D 2300/6033: Ceramic matrix composites [CMC]
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

## Claims

### Claim 1

A device for attaching blades to a rotor disk of a turbine engine, comprising:
a rotor disk provided at an outer periphery thereof with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the rotor disk;
a plurality of blades, each of the blades having a respective root mounted in a respective slot of the rotor disk; and
at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between and up to the front and rear faces of the rotor disk so as to attach the blades to the rotor disk,
wherein the blades are made of composite material and the rotor disk is metallic.

### Claim 2 (depends on 1)

A device according to claim 1, having at least two pins passing through the roots of at least two adjacent blades, said pins being regularly spaced apart from one another and extending in directions that are substantially parallel.

### Claim 3 (depends on 1)

A device according to claim 1, wherein each pin passes through the roots of three adjacent blades.

### Claim 4 (depends on 1)

A device according to claim 1, wherein each pin emerges in the front and rear faces of the rotor disk in the teeth of the disk.

### Claim 5 (depends on 1)

A device according to claim 1, wherein each pin is made of a metal material.

### Claim 6 (depends on 1)

A device according to claim 1, wherein each pin presents a cross section of circular, elliptical, or rectangular shape.

### Claim 7 (depends on 1)

A device according to claim 1, wherein each pin is of straight or curved shape.

### Claim 8 (depends on 1)

A device according to claim 1, wherein the root of each blade presents at least one hole for passing a pin, the hole having surface treatment or an insert.

### Claim 9 (depends on 8)

A device according to claim 8, wherein a zone of the root of each blade in the vicinity of the holes are reinforced.

### Claim 10 (depends on 1)

A device according to claim 1, wherein each blade is made of ceramic matrix composite material.

### Claim 11 (depends on 1)

A low pressure turbine for a turbojet, the turbine having at least one device according to claim 1.

### Claim 12 (depends on 11)

A turbojet including a low pressure turbine according to claim 11.

### Claim 13 (depends on 1)

A device according to claim 1, wherein each pin passes through a channel constituted by holes formed in the teeth of the rotor disk and holes formed in the roots of the blades, the channel having a first end at the front face of the rotor disk and a second end at the rear face of the rotor disk.