| 摘要 |
PROBLEM TO BE SOLVED: To arrange a local fattening in a section of an airfoil called as a root; and to provide a preferable blade with respect to a reference. SOLUTION: The monocrystalline turbomachine blade that is cast and directionally solidified, comprising: the airfoil 11 with a leading edge BA, a pressure face FI, a suction face FE, a trailing edge BF, a skeleton S and having a longitudinal axis ZZ, the faces FI and FE having a neck line, respectively a pressure face neck CI and a suction face neck CE relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece 20 of the airfoil, such as a heel or a platform, having an airfoil end face 21, on the stream side, forming an angle with the axis ZZ; and a connection zone 11E forming the fattening of the airfoil between the airfoil 11 and the airfoil end face. COPYRIGHT: (C)2009,JPO&INPIT
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