| CPC F01D 5/186 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/30 (2013.01); F05D 2240/303 (2013.01); F05D 2240/304 (2013.01); F05D 2250/185 (2013.01); F05D 2260/202 (2013.01); F05D 2260/22141 (2013.01)] | 13 Claims |
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1. A turbine blade for use in a gas turbine engine, the turbine blade comprising:
an airfoil with a concave sidewall and a convex sidewall extending spanwise between a platform and a blade tip, and chordwise between a leading edge and a trailing edge;
wherein internal surfaces of the airfoil define an internal cooling passage within the airfoil extending between a cooling air inlet and a plurality of air outlets, the internal cooling passage comprising:
a serpentine channel comprising a leading edge channel, an intermediate channel, a trailing edge channel, a plurality of turbulators positioned along an internal surface of a sidewall, and a plurality of leading edge turbulators positioned along a leading edge of the leading edge channel;
wherein the plurality of turbulators extend from a first pull plane into the serpentine channel, and at least a portion of the plurality of leading edge turbulators extend from a second pull plane into the serpentine channel; and
wherein the second pull plane is offset from the first pull plane by a compound angle comprising a first angle and a second angle.
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