Cleat for open-work blade foot

Patent metadata

Field	Value
Publication number	US-9453414-B2
Application number	US-201314044208-A
Country	US
Kind code	B2
Filing date	Oct 2, 2013
Priority date	Oct 10, 2012
Publication date	Sep 27, 2016
Grant date	Sep 27, 2016

Abstract

A cleat for a blade foot of a blade of a propeller of a turboengine is provided. The cleat allows the discharge of ventilation airflow of the blade foot.

First claim

The invention claimed is:

1. A propeller for a turboengine comprising:
a blade including a foot;
a pivot including a groove which receives the foot of the blade;
a support ring provided with a housing receiving the pivot; and
a cleat placed between the pivot and the blade foot,
wherein the pivot includes a first inner communicating channel extending between a first side of the pivot and the groove, and a second inner communicating channel extending between the groove and a second side of the pivot, and
wherein the cleat includes a discharge channel which allows fluid communication of airflow between the blade foot and the first and second inner communicating channels.

2. The propeller as claimed in claim 1 , wherein the discharge channel is located under the blade foot.

3. The propeller as claimed in claim 2 , wherein the discharge channel includes an axial discharge channel.

4. The propeller as claimed in claim 2 , the discharge channel includes a lateral discharge channel.

5. The propeller as claimed in claim 1 , wherein the pivot is equipped with a counterweight system provided with an inner channel of the airflow intended to come into contact with the cleat.

6. The propeller as claimed in claim 5 , wherein the inner channel includes an inner end which terminates on the pivot and at least one of an introduction end and an ejection end of the airflow.

7. The propeller as claimed in claim 5 , wherein the counterweight system is made of composite material.

8. The propeller as claimed in claim 1 , wherein at least one of the blade, the cleat, and the pivot is made of composite material.

9. A turboengine comprising a propeller as claimed in claim 1 .

10. The turboengine as claimed in claim 9 , said propeller being located downstream of a combustion chamber of said turboengine.

11. The turboengine comprising a pair of open contrarotating propellers, each of the two propellers being said propeller as claimed in claim 1 .

Assignees

• Snecma

Inventors

• Tajan Sebastien
• Jacquemard Christophe

Classifications

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• Y02T50/66

  Cross-Sectional Technologies · mapped topic