Patent ID: 7980817

Claim:
A gas turbine engine vane comprising: a first member having: a first surface section forming a suction side of an airfoil of the vane; a second surface section forming leading and trailing portions of a pressure side of said airfoil; and a third surface section forming a well between said leading and trailing portions; and a second member secured to the first member and having a first surface section forming an intermediate portion of the pressure side, wherein: the well comprises a leading recess and a trailing shoulder; the second member has: a second surface section generally opposite the second member first surface section and having a first portion secured to the trailing shoulder; and a leading projection captured by the recess; the trailing shoulder forms a partial perimeter rebate around the well with the rebate extending along a trailing boundary, an inboard boundary, and an outboard boundary of the well; and the recess is beneath a downstream-projecting lip portion, the leading projection protruding forward/upstream recessed below the second surface along the first member.