Propeller for an aircraft engine comprising means for reducing noise at middle and high frequencies and improving the acoustic perception

Patent metadata

Field	Value
Publication number	US-9540094-B2
Application number	US-201313894076-A
Country	US
Kind code	B2
Filing date	May 14, 2013
Priority date	May 16, 2012
Publication date	Jan 10, 2017
Grant date	Jan 10, 2017

Abstract

Enriching and balancing the acoustic spectrum radiated by a propeller by introducing a differential pitch angle on certain blades of the propeller. Modifying the acoustic spectrum makes it possible to render the propeller noise more pleasant to the human ear.

First claim

The invention claimed is:

1. A turbomachine for aircraft, comprising two propellers, said propellers being coaxial and arranged one behind the other along an axis of said turbomachine, and said propellers rotating in respective opposite directions, each of said propellers comprising a hub in rotation according to an axis of rotation of the propeller and at least 4 blades distributed around said hub, with each of the blades comprising a blade root by means of which the blade is fixed on said hub of the propeller and an aerodynamic portion extending radially outwardly away from the axis of rotation of the propeller from the root of the blade, with a pitch angle defined for each blade as being the angle that a chord of an aerofoil of the radially inner end of the aerodynamic portion of the blade forms with a plane perpendicular to the axis of rotation of the propeller, wherein in each of said propellers the at least 4 blades comprises a first plurality of blades and a second plurality of blade, each blade in the first plurality of said at least 4 blades uniformly distributed around said hub has a first pitch angle that differs from a second pitch angle of each blade in the second plurality of said at least 4 blades uniformly distributed around said hub wherein adjacent blades of said at least 4 blades are free from engagement along respective aerodynamic portions of said adjacent blades.

2. The turbomachine according to claim 1 , wherein all of the blades of each of said propellers are distributed uniformly around said hub of the propeller.

3. The turbomachine according to claim 2 , wherein each of said propellers comprises a quantity of blades designated by a variable n, wherein n is a non-prime number.

4. The turbomachine according to claim 3 , wherein the maximum difference in pitch angle between any two blades each of said propellers is less than or equal to 5°.

5. The turbomachine according to claim 4 , wherein the at least 4 blades of at least one of the propellers comprises at least 6 blades wherein each blade in a third plurality of said at least 6 blades has a third pitch angle that differs from the first pitch angle and the second pitch angle.

6. The turbomachine according to claim 3 , wherein the at least 4 blades of at least one of the propellers comprises at least 6 blades wherein each blade in a third plurality of said at least 6 blades has a third pitch angle that differs from the first pitch angle and the second pitch angle.

7. The turbomachine according to claim 2 , wherein the maximum difference in pitch angle between any two blades each of said propellers is less than or equal to 5°.

8. The turbomachine according to claim 7 , wherein the at least 4 blades of at least one of the propellers comprises at least 6 blades w wherein each blade in a third plurality of said at least 6 blades has a third pitch angle that differs from the first pitch angle and the second pitch angle.

9. The turbomachine according to claim 2 , wherein the at least 4 blades of at least one of the propellers comprises at least 6 blades wherein each blade in a third plurality of said at least 6 blades has a third pitch angle that differs from the first pitch angle and the second pitch angle.

10. The turbomachine according to claim 1 , wherein the maximum difference in pitch angle between any two blades each of said propellers is less than or equal to 5°.

11. The turbomachine according to claim 10 , wherein the at least 4 blades of at least one of the propellers comprises at least 6 blades wherein each blade in a third plurality of said at least 6 blades has a third pitch angle that differs from the first pitch angle and the second pitch angle.

12. The turbomachine according to claim 1 , wherein the at least 4 blades of at least one of the propellers comprises at least 6 blades wherein each blade in a third plurality of said at least 6 blades has a third pitch angle that differs from the first pitch angle and the second pitch angle.

Assignees

• Airbus Operations Sas
• Aibus Operations (Sas)

Inventors

• Negulescu Camil
• Omais Magdi

Classifications

• B64C11/48 Primary

  Units of two or more coaxial propellers · CPC title

• Y02T50/66

  Cross-Sectional Technologies · mapped topic

• B64D2027/005

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

• B64C11/18

  Aerodynamic features · CPC title

• Y02T50/60

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