Patent ID: 8777583

Claim:
A turbine blade of a gas turbine engine, the blade comprising: a first subcomponent comprising an airfoil portion and a nub, the airfoil portion having a dominant axis and the nub comprising a base that has a cross-section that is wider than the airfoil portion, the first subcomponent being formed of a ceramic-based material; and a second subcomponent comprising a casting formed of a metallic material and attached to the first subcomponent by casting the metallic material in-situ around the base of the nub of the first subcomponent, the second subcomponent comprising a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent; and at least one hole through the nub, wherein some of the metallic material is within the hole and interconnects regions of the second subcomponent that are separated by the nub.