Patent ID: 9611748
Date: 2017-04-04
CPC Classifications: B22C,F01D,F05D

Claim:
1. A stationary airfoil for a bi-cast turbine engine component, the stationary airfoil comprising: a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall; and an end portion shaped with a pair of inwardly deformable opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component, each one of the pair of inwardly deformable opposing flanges curve radially outward from a respective one of the pressure sidewall and the suction sidewall to define the end portion and to define an interlocking feature, the slip joint permitting radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction, wherein the end portion comprises a generally C-shaped end portion, and the inwardly deformable opposing flanges define a terminal end of the end portion.