Turbine blade with dual serpentine cooling

Abstract

A turbine rotor blade with a low cooling flow serpentine circuit to provides cooling for the airfoil. The circuit includes a three pass aft flowing serpentine circuit that begins at the airfoil mid-chord region and connects to a series of multiple impingement cooling holes formed within the trailing edge region. A double pass forward flowing serpentine circuit then connects with the triple pass aft flowing serpentine circuit to provide cooling for the leading edge region and is connected to a showerhead arrangement for discharging film cooling air. A blade tip cooling channel connects with the last leg of the double pass forward flowing serpentine to form a 6-pass serpentine flow cooling circuit for the entire blade. Since only the leading edge serpentine channel discharges film cooling air, the serpentine circuit can make use of low cooling flow to provide cooling for the entire blade.

Dependencies are inferred from the claim text.