Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
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United States of America Patent
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-
Jan 23, 2007
Issued Date -
N/A
app pub date -
Jan 21, 2005
filing date -
Dec 26, 2002
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.
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