| 摘要 |
<p>A turbomachinery blade for a gas turbine engine is provided and includes an airfoil extending between a leading edge and a trailing edge. In one embodiment the turbomachinery blade is a compressor blade. The blade can include a platform attached to the airfoil on one side, the other side being attached to a stalk having a lower attachment portion useful for being received in a compressor disk. The blade includes an undercut beneath a portion of the airfoil, preferably beneath the leading edge and/or trailing edge of the airfoil. In one form the undercut is located in a corner of the platform and extends partially along two sides of the platform.</p> |
