The Boeing Company

Joseph M Baskin

Gary E Miller

Wayne Wiesner

A fixed pitch wind turbine rotor (18) is teeter mounted (76, 78, 80) onto a low speed input shaft (44) which is connected to the input (58) of a step-up transmission (46). The output (48) of the transmission (46) is connected to a rotary pole amplitude modulated induction machine (42) which is operable as a generator at a plurality of discreet speeds of rotation and is also operable as a startup motor for the rotor. A switch (45) responsive to the rotational speed of the wind turbine rotor switches the generator from one speed of operation to the other. The rotor hub (72) and the inner body portions (71) of two blades (68, 70), which extend radially outwardly in opposite directions from the hub (72), are constructed from steel. The outer end portions (73) of the blade (68, 70) are constructed from a lighter material, such as wood, and are both thinner and narrower than the remainder of the rotor. The outer end section (73) of each blade (68, 70) includes a main body portion and a trailing edge portion (104) which is hinge-connected to the main body portion. Each blade (68, 70) includes a centrifugal force operated positioning means (98, 100) which normally holds the drag brake section (104) in a retracted position, but operates in response to a predetermined magnitude of centrifugal force to move the drag brake (104) section into its deployed position. Each blade has an airfoil cross section and each blade (68, 70) has a plus twist inner portion adjacent the hub (72) changing to first a zero twist and then a minus twist as it extends radially outwardly from the hub (72).

Wind powered system for generating electricity

Wind turbine rotor

A load absorbing elastic member or members is incorporated in the design of a rotor blade to assist in reducing flapwise and chordwise bending moments, torsional loading, and to reduce or eliminate the control system loads induced by rotor blade moment stall. In all its embodiments, the load absorbing elastic member has operatively associated therewith a constraining member which serves as a strain amplifier permitting the load absorbing elastic member to achieve its purpose effectively.

Rotor blade internal damper

A rotor pitch control mechanism for use with bearingless helicopter rotors is disclosed. The disclosed mechanism eliminates the requirement for vertical motion of the pitch link, thus alleviates the bearingless rotor problem of flapwise motion of the rotor blade in response to pitch control actuator forces. Stabilizing pitch-flap coupling and blade flap restraint is provided.

Growing community of inventors

Bala Cynwyd, PA, United States of America

Joseph M Baskin