Composite reinforcement of metallic airfoils

Details Composite reinforcement of metallic airfoils Composite reinforcement of metallic airfoils

1976-12-22

1978-10-03

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Laminated, embedded member or encased material

416500, 416224, F01D 516

Patent

active

041181476

ABSTRACT:
A method of fabricating a turbomachinery blade is provided whereby high stress levels associated with stripe mode resonance can be avoided. Once the nodal pattern for an objectionable stripe mode resonance condition of a metallic blade is determined by conventional means, a portion of the blade parent metal near the tip is replaced with a composite patch, the composite patch comprising elongated filaments embedded in a matrix material. The chordwise extent of the patch includes the nodal points at the objectionable stripe mode resonance condition and the filament orientation is chordwise to enhance chordwise stiffness.

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patent: 3566493 (1971-03-01), Poucher et al.
patent: 3796513 (1974-03-01), Jonas

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