Abstract: One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag.

Abstract: A propeller blade for rotation about a hub assembly is provided, wherein the propeller blade defines a radial direction along its length from a blade root to a blade tip, the propeller blade comprising: a radially inner region; a radially outer region located between the blade root and the blade tip at a position where rotational forces on the blade are sufficient, in use, to remove ice from an uncoated blade; a coating disposed at least along a leading edge of the propeller blade, the coating comprising an icephobic material, wherein the coating extends along the propeller blade from the radially inner region to the radially outer region.

Abstract: A propeller blade for rotation about a hub assembly is provided, wherein the propeller blade defines a radial direction along its length from a blade root to a blade tip, the propeller blade comprising: a radially inner region; a radially outer region located between the blade root and the blade tip at a position where rotational forces on the blade are sufficient, in use, to remove ice from an uncoated blade; a coating disposed at least along a leading edge of the propeller blade, the coating comprising an icephobic material, wherein the coating extends along the propeller blade from the radially inner region to the radially outer region.

Abstract: One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag.

Abstract: A propeller blade assembly (1) comprises a plurality of propeller blades (10) each connected to a hub (2) via at least one bearing assembly (3,4). Each of the blades (10) and the bearing assemblies (3,4) is preloaded, wherein the preload is applied over a preload path which includes a blade root portion (11) of each blade (10) and the bearing assemblies (3,4), and a spring (6) is provided in the preload path. In the event of wear of the components of the propeller blade assembly, the spring (6) maintains the preload force. A method of applying the preload to the propeller blade assembly (1) is also disclosed.