Structural preform layers of multiple rigid unidirectional strength elements or rods are constructed and arranged for use in fabricating load-bearing support structures and reinforcements of wind turbine blades. Individual preform layers include multiple elongate unidirectional strength elements or rods arranged in a single layer along a longitudinal axis of the preform layer. Each preform layer includes one or more fibrous carrier layers to which the multiple strength elements or rods are joined and arranged in the single layer. Each strength element or rod is longitudinally oriented and adjacent to other elements or rods. Individual strength elements or rods include a mass of substantially straight unidirectional structural fibers embedded within a matrix resin such that the elements or rods have a substantially uniform distribution of fibers and high degree of fiber collimation. The relative straightness of the fibers and fiber collimation provide strength elements or rods and the preform layers with high rigidity and significant compression strength.

Wind turbine rotor blade components and methods of making same

A composite material blade is provided having a twin longeron and twin box structure with laminated honeycomb sandwich coverings, including a front leading edge longeron of a C shaped section, a central longeron with two sole pieces at the ends of a transverse web with honeycomb filling sandwiched between lateral sheets, and laminated coverings made from honeycomb panels sandwiched between external and internal sheets formed by stacking layers of fiber fabric, so as to define two boxes filled with very light foam cores, the sole pieces being integrated in the coverings which are joined at the level of the trailing edge by a rider in the form of a foam wedge.

Composite material blade with twin longeron and twin box structure having laminated honeycomb sandwich coverings and a method of manufacturing same

A propeller blade spar/foam subassembly is manufactured by disposing a lamination of prepreg within a mold, closing the mold about a spar and injecting foam into mold cavities formed at the lead edge and the trailing edge of the spar.

Propeller blade subassembly and method for making a propeller blade subassembly

Rotor blade stowing system for stowing rotor blades that conserves storage space without adding significant weight or cost to the aircraft. The system includes a rotary actuator disposed on a blade grip member. A rotor blade is pivotally connected to the blade grip member. The rotary actuator is operably coupled to a blade pivoting cam and a locking cam. The system includes a cam follower linkage which has a first end which includes a blade pivoting cam follower and a locking cam follower and a second end. The blade pivoting cam follower follows the blade pivoting cam. The locking cam follower follows the locking cam. The second end of the cam follower linkage is coupled to the blade grip member. The system includes a shaft rotatably coupled to the blade grip member, a locking linkage bell crank operably coupled to the shaft, a delay cam coupled to the blade grip member, and a locking linkage idler operably coupled to the locking linkage bell crank. The locking linkage idler includes a delay cam follower that follows the delay cam. The system includes a locking linkage which has a first end coupled to the locking cam and a second end coupled to the locking linkage idler.

Rotor blade stowing system

The method includes the following steps: producing a preform of the blade comprising a blade root section for connecting to a hub and an aerodynamically profiled main blade section, the preform including, in the blade root section, a pile of fabrics transverse to the span axis of the blade projecting with respect to the blade root section, so as to form a pitch control lever; arranging the preform in an injection mold; injecting a thermosetting liquid resin into the mold; and heating the mould to make the thermosetting resin set.

Method for manufacturing a variable-pitch composite blade for a helicopter rotor

The invention provides a helicopter rotor blade made from a composite material whose multistrut resistant framework adjacent the leading edge is disposed so as to form two superimposed compartments.

Helicopter rotor blade made from a multispar composite material with torsion compartments and a process for manufacturing same

The invention relates to a pay for rotor helicopter composite material whose skeleton resistant multilongeron adjacent the leading edge (4) is arranged so as to form two superposed chambers (2 and 3). Application to the construction of aircraft.

Multispar composite helicopter rotor blade with torsion box, and its manufacturing process

L'invention concerne une paie pour rotor d'helicoptere en materiau composite dont l'ossature resistante multilongeron voisine du bord d'attaque (4) est disposee de facon a former deux caissons superposes (2 et 3) Application a la construction des aeronefs

Michel Bost

Papers

Helicopter rotor blade made from a multispar composite material with torsion compartments and a process for manufacturing same

Multispar composite helicopter rotor blade with torsion box, and its manufacturing process

Pale pour rotor d'hélicoptère en matériau composite multilongeron à caissons de torsion et son procédé de fabrication