|1. An internally cooled airfoil for a gas turbine engine, comprising a hollow airfoil body including a pressure sidewall and
a suction sidewall extending chordwise from a leading edge to a trailing edge, the pressure and suction sidewalls having an
internal surface bounding a core cavity, an insert mounted in the core cavity in spaced-apart relationship with said internal
surface to define a cooling gap therewith, and a plurality of standoffs projecting from said internal surface of said pressure
and suction sidewalls into the cooling gap toward the insert, a plurality of trip-strips projecting from said internal surface
of the pressure and suction sidewalls, the trip-strips being intersperse between adjacent standoffs and extending laterally
with respect thereto, wherein the plurality of standoffs include standoffs in a mid-chord area of the pressure and suction
sidewalls, the trip-strips intersecting the standoffs in the mid-chord area.