A large and highly tapered and twisted turbine rotor blade for a large frame and heavy duty industrial gas turbine engine, where the blade includes a main spar with multiple impingement chambers extending along the chordwise direction of the blade, and with a thin thermal skin bonded to the main spar to form an airfoil section for the blade. The chordwise impingement channels are separated by ribs to form multiple chambers in the spanwise direction from the root to the blade tip. These compartmented impingement channels formed along the airfoil spanwise direction can be used for tailoring the gas side pressure variation in the spanwise direction, and individual impingement channels can be designed based on the airfoil local external heat load to achieve a desired local metal temperature. With this cooling circuit, the usage of cooling air is maximized for a given airfoil inlet gas temperature and pressure profile.