Propeller assembly with at least two propeller blades

Patent metadata

Field	Value
Publication number	US-10486794-B2
Application number	US-201715471236-A
Country	US
Kind code	B2
Filing date	Mar 28, 2017
Priority date	Apr 1, 2016
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising associated leading and trailing edges that define a respective chord and quarter chord line thereof, wherein the common pitch axis is arranged with a predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, and wherein the associated connection means is adapted to enable, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis.

First claim

What is claimed is:

1. A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising a leading edge and a trailing edges that define a chord and a quarter chord line thereof,
wherein the common pitch axis has an upstream predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, the upstream predetermined offset being in a region defined between the leading edge and the quarter chord line of each one of the at least two propeller blades to produce an additional momentum next to a blade's quarter chord line moment, resulting from a rotation of each one of the at least two propeller blades around the quarter chord line and wherein the associated connection means enables, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis in response to aerodynamic forces acting on the at least two propeller blades.

2. The propeller assembly according to claim 1 , wherein at least in operation the passive pitch adjustment homogenizes at least approximately an underlying lift distribution generated by the at least two propeller blades in operation.

3. The propeller assembly according to claim 1 , wherein the common pitch axis is arranged at least approximately in parallel to the quarter chord line of each one of the at least two propeller blades.

4. The propeller assembly according to claim 3 , wherein further to the upstream predetermined offset, the common pitch axis has a predetermined height offset relative to a height position of the quarter chord line of each one of the at least two propeller blades.

5. The propeller assembly according to claim 1 , wherein a pitching moment transfer device is provided, the pitching moment transfer device being adapted to transfer a pitching moment generated on one of the at least two propeller blades during the passive pitch adjustment in operation to the other one of the at least two propeller blades.

6. The propeller assembly according to claim 5 , wherein the pitching moment transfer device defines a rigid link between the at least two propeller blades.

7. The propeller assembly according to claim 6 , wherein the pitching moment transfer device comprises at least one plate-shaped support that is rigidly mounted to each one of the at least two propeller blades.

8. The propeller assembly according to claim 1 , wherein the passive pitch adjustment of the at least two propeller blades in operation is achieved by a rotation of the at least two propeller blades around the common pitch axis, wherein associated rotation damping means are provided for damping the rotation of the at least two propeller blades around the common pitch axis.

9. The propeller assembly according to claim 8 , wherein the associated rotation damping means comprises at least one of bell hiller weights and aerodynamic paddles.

10. The propeller assembly according to claim 1 , wherein the associated connection means are mounted in a rotatable manner to an associated propeller mast.

11. The propeller assembly according to claim 10 , wherein bearings are provided for mounting the associated connection means to the associated propeller mast.

12. The propeller assembly according to claim 1 , wherein the predetermined offset of the common pitch axis relative to the quarter chord line of each one of the at least two propeller blades defines an offset angle (α,β).

13. The propeller assembly according to claim 1 , wherein the associated connection means are interconnecting at least four propeller blades.

14. An aircraft comprising a propeller assembly according to claim 1 .

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Kiesewetter Uwe
• Haisch Stefan
• Bebesel Marius
• Mores Sebastian

Classifications

• B64C27/54

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title

• B64C27/43 Primary

  see-saw type, i.e. two-bladed rotor · CPC title

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• B64C27/467

  Aerodynamic features · CPC title

• B64C11/008

  characterised by vibration absorbing or balancing means · CPC title