A robust multiple-walled, multi-pass, high cooling effectiveness cooled
turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded
turbine rotors. The vane or blade design allows the
turbine inlet temperature to increase over
current technology levels while simultaneously reducing turbine cooling to low levels. A multi-wall cooling
system is described, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade's pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to
specific heat load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the
suction surface is an independent rearward flowing serpentine). The cooling air for the independent circuits is supplied through separate passages at the base of the vane or blade. The cooling air follows intricate passages to feed the serpentine thin outer wall passages, which incorporate pin fins, turbulators, etc. These passages, while satisfying the aero / thermal / stress requirements, are of a manufacturing configuration that may be cast with
single crystal materials using
conventional casting techniques.