A blade (102) of a gas turbine engine may comprise a cavity (134) defined, at least partially, by a first interior surface of the blade (102) and by a second interior surface of the blade (102). A first rib (140) and a second rib (142) may extend from the first interior surface. A third rib may extend from the second interior surface and may be located between the first rib (140) and the second rib (142). A bulkhead rib (150) may traverse the cavity (134) and may separate the cavity (134) into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity (134).
BLADE WITH DAMPING STRUCTURES
SCHAUFEL MIT DÄMPFUNGSSTRUKTUREN
LAME COMPORTANT DES STRUCTURES D'AMORTISSEMENT
2021-04-21
Patent
Elektronische Ressource
Englisch
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