Tip fabrication for rotor blade or stator vane airfoil
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United States of America Patent
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Feb 14, 2017
Grant Date -
Jun 11, 2015
app pub date -
Jun 13, 2013
filing date -
Jun 13, 2012
priority date (Note) -
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Abstract
A method comprises identifying an engine-run tip position for an airfoil having a tip section and a root section. The engine-run tip position is displaced and rotated with respect to a nominal position, as defined with respect to the root section before engine running. A airfoil tip is formed on the airfoil, and a machining datum is defined adjacent the airfoil tip. The tip section is translated and rotated to locate the airfoil tip in the nominal position, without respect to a location of the root section. The tip section is restored to a nominal profile by machining the airfoil tip along a machining path defined with respect to the machining datum, wherein the machining path is independent of the displacement and rotation of the engine-run tip position and independent of the position of the root section.
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