Internally cooled turbine blade

An internally cooled turbine blade for use in a gas turbine engine, the internally cooled 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, and a plurality of turbulators;
• wherein two adjacent rows of the plurality of turbulators are positioned within the trailing edge channel;
• wherein:
• the leading edge channel is positioned adjacent the leading edge of the airfoil;
• the trailing edge channel is positioned adjacent the trailing edge of the airfoil;
• and
• the intermediate channel is positioned between the leading edge channel and the trailing edge channel;
• wherein the leading edge channel and the intermediate channel are separated by a first dividing wall that extends from a blade base toward the blade tip and wherein the first dividing wall includes a first radially outer end configured to turn cooling air flowing in the leading edge channel from a platform towards the blade tip into the intermediate channel such that the cooling air flows in the intermediate channel from the blade tip towards the platform, and
• wherein the trailing edge channel and the intermediate channel are separated by a second dividing wall that extends from the platform toward the blade tip and wherein the second dividing wall includes a second radially inner end configured to direct cooling air flowing in the intermediate channel from the blade tip to the platform into the trailing edge channel such that the cooling air flows in the trailing edge channel from the platform towards the blade tip.