Composite aerodynamic rotor blade assembly

Details Composite aerodynamic rotor blade assembly Composite aerodynamic rotor blade assembly

1978-05-08

1982-02-23

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Formed with main spar

416230, B64C 2746

Patent

active

043167012

ABSTRACT:
What follows is a description of a composite aerodynamic rotor blade assembly which has been optimized from the standpoint of both fabrication cost and structural integrity. The rotor blade is fabricated using fewer overall assemblies to optimize cost and includes an aft fairing structure which is uniquely characterized in that it includes not only the typical elements of an aft fairing structure of the composite blade, but the spar heel as well. In assembly the skin members of the aft fairing structure are secured between the spar heel and the cap member of the assembly. This insures a fail-safe design and in this way the skin members are enabled to carry load effectively. The deicing blanket is assembled with the spar and cap member so that its supporting structural material serves as a load carrying member. Also, the spar, the inboard termination of the cap member, and the spar heel together form the root end of the rotor blade into which the torsion splices are formed.

REFERENCES:
patent: 2694458 (1954-11-01), Stevens
patent: 2771144 (1956-11-01), Lasserre et al.
patent: 3144907 (1964-08-01), Lubben et al.
patent: 3237697 (1966-03-01), Ford et al.
patent: 3333642 (1967-08-01), Kee
patent: 3528753 (1970-09-01), Dutton et al.
patent: 3552881 (1971-01-01), Rogers et al.
patent: 3713751 (1973-01-01), Fradenburgh et al.
patent: 3749517 (1973-07-01), Galli
patent: 4095322 (1978-06-01), Scarpati et al.

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