Abstract: A gas turbine engine airfoil is cast around a core having a plurality of legs to form matching flow channels in the airfoil. The legs have a tie extending therebetween to maintain alignment. And, the tie is relocated along the core span to reduce differential static pressure of the cooling air across the resulting tie hole formed by the core tie.

Abstract: A shroud includes a panel having leading and trailing edges and inner and outer surfaces extending therebetween. A cooling passage extends through the panel from adjacent the leading edge to an intermediate location and is generally parallel to the inner and outer surfaces. The cooling passage has an inlet for receiving cooling air from adjacent the panel outer surface, a plurality of spaced apart turbulators disposed adjacent to the panel inner surface, and an outlet disposed at the leading edge for discharging the cooling air from the passage.

Abstract: A turbine blade is provided which includes an airfoil section having a leading edge flow region and a trailing edge flow region. The leading edge flow region includes an inner cavity having a serpentine geometry and first and second air inlets. The first air inlet is at one end of the inner cavity and is coupled to a first conduit which supplies air coolant thereto. The leading edge flow region also includes a leading edge cavity having a plurality of air film holes at the leading edge of the blade. The leading edge cavity is coupled to the inner cavity by impingement holes therebetween. The leading edge flow region further includes a refresher passageway which connects the first conduit at the base of the blade with the second inlet of the inner cavity. The refresher passageway refreshes the airflow in the inner cavity after the airflow has flowed part way through the inner cavity and has become warmed.