Segmented ring blade retainer
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United States of America Patent
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May 22, 2001
Grant Date -
N/A
app pub date -
Oct 26, 1998
filing date -
Oct 26, 1998
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A retainer for a rotor disk assembly of a gas turbine engine forms one aspect of the present invention. The retainer prevents axial displacement of a plurality of blades coupled to the rotor disk. The retainer includes a plurality of retaining segments and a locking segment. The locking segment is positioned between two of the retaining segments to define a first joint and a second joint. The first and second joints are offset a distance from and are substantially parallel to an axis extending through the center of the rotor disk assembly. The retainer may also be provided with means for preventing displacement of the retainer towards the center of the rotor disk assembly.
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