Patent attributes
A turbine blade or airfoil used in a gas turbine engine, the blade having a single cooling air flow path from leading edge to the trailing edge formed from a series of impingement cavities each connected by impingement holes. the series of impingement cavities are formed to alternate from a pressure side cavity to a suction side cavity, and the impingement holes are therefore offset at about 90 degrees, resulting in more impingement cavities being crowded into the length of blade and the impingement holes providing a jet of cooling air directed to a smaller impingement area and at about a head-on direction to the hot section of the cavity. The first impingement cavity is located at the leading edge as is supplied with cooling air from the exterior source, while the last impingement cavity in the series is located in the trailing edge region and includes a plurality of exit holes extending along the trailing edge to discharge the cooling air from the circuit. a greater number of impingement cavities are used in the same length of blade, and a more concentrated impingement jet is directed at the hottest surface of the cavity to provide improved cooling heat transfer coefficient.