Damper configured turbine blade
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United States of America Patent
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Jun 15, 2010
Grant Date -
Oct 16, 2008
app pub date -
Apr 10, 2007
filing date -
Apr 10, 2007
priority date (Note) -
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status (Latency Note)
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Abstract
A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.
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