The invention belongs to the technical field of blade
investment casting, and relates to a method for eliminating
grain boundary cracks of a large-size directional hollow blade, which is used for
casting directional column
crystal working blades of
gas turbines and the like with the transverse size exceeding 130mm. The method comprises the following steps of: when a
wax mold is trimmed, adhering a cylindrical
wax stick to a mold core positioning position extending out of a
tail edge; the
coating property of the enhanced shell
slurry is used for increasing the thickness of the shell at the position; when the modules are combined,
wax pattern baffles are arranged outside the front and
tail edges, so that the heat dissipation speed of the front and
tail edges is reduced; and during
directional solidification, the standing time of the
alloy liquid after
casting is prolonged so as to slow down the solidification rate of the initial position of the blade tip, so that cracks at the directional
grain boundary caused by overlarge transverse solidification stress are eliminated, and the
casting qualification rate of the large-size directional gas
turbine working blade is improved.