Abstract: Methods and apparatus for gas turbine frame flow path hardware cooling are disclosed. An example engine fan case includes an outer band and an inner band, the outer band and the inner band connected using a double-walled vane, the vane including openings to pass cooling air flow from the outer band to an airfoil of the fairing, and an end segment seal, the seal formed on an edge of the fairing using an auxetic material.

Abstract: A turbine blade has a trailing end and a leading end and a tip. A gutter is formed in the tip and extends to an exit defined in a region of the trailing end of the blade. The gutter is defined at least in part by a floor, and the floor defines a decreased depth in a region proximal to the exit than in a region distal to the exit.