Ratier-figeac Sas

Ratier Figeac

Bruno Petellaz

Stanislas Tutaj

Pascal Amat

Abdellah El Haloui

Catherine Delmas

A method for monitoring the health of propellers in an aircraft is provided. The method includes receiving pressure waves generated by at least one rotating propeller and analysing data corresponding to the received pressure waves to detect tonal noise which is within a selected frequency range. If tonal noise at harmonics of the propeller rotational frequency within the selected frequency range is detected within the selected frequency range, it is established that the health of at least one propeller may be impaired and an alert is created for inspection and maintenance to take place.

Propeller health monitoring

A blade pitch adjustment system comprising a yoke arranged to be moved in a first direction in response to an actuator; a plurality of trunnion pins arranged to be attached to a respective propeller blade; a respective contact surface between the yoke and each trunnion pin such that movement of the yoke causes rotation of the blades, and wherein the contact surfaces differ so as to create different angles of rotation of the blades at different points of yoke movement or actuator stroke.

Blade pitch control

A blade includes an aerodynamic portion () and an assembly of the aerodynamic portion to a blade shank retaining the aerodynamic portion in a radial direction (). The blade shank includes at least one passage restriction in at least one retention direction orthogonal to the radial direction, having a restricted width allowing the aerodynamic portion () to pass through. The base of the aerodynamic portion () has an overall dimension which is strictly greater than the restricted width so that, in the event of rupture of the assembly, the base is able to come into abutment against the passage restriction so as to retain the aerodynamic portion () in the blade shank ().

Blade anchored securely in radial translation, propeller, turbine engine and aircraft

A propeller blade includes a foam core having a groove formed therein, a fibrous material filling at least a portion of the groove and a structural layer that surrounds the fibrous material and at least a portion of the foam core.

Propeller blade with spar rib

A propeller blade includes an aerodynamic portion and a blade shank, a hub assembly () which provides anchoring in a hub, a blade shank assembly of the aerodynamic portion, a safety device including a safety element () which extends from a distal assembly in the aerodynamic portion to a proximal assembly () in the blade shank and which is adapted to be able to anchor the aerodynamic portion in the blade shank, wherein the blade shank assembly is anchored radially outside the hub assembly, the proximal assembly is anchored to the blade shank radially inside the hub assembly, and the distal assembly and/or the proximal assembly has a strictly positive radial clearance ().

Blade with redundant anchoring in a hub, propeller, turboprop engine and aircraft

The invention relates to a propeller blade which comprises a hollow casing () forming an extrados () and an intrados () which extend from a blade shank to a free end in the direction of the span, and a framework which is arranged in the hollow casing () and comprises a box spar (), having a plurality of soles () in surface contact with the hollow casing () so as to provide structural support for the hollow casing (), and at least two cavities () which are spaced apart in the direction of the chord (), wherein the propeller blade further comprises at least two reinforcing spars () which extend between the framework and the hollow casing.

Growing community of inventors

Beduer, France

Bruno Petellaz