Patent ID: 7210906

Claim:
An internally cooled airfoil for a gas turbine engine, the airfoil having a hollow section and a trailing edge, the airfoil comprising: a plurality of partition walls located in the hollow section and defining at least two internal cooling air passages substantially parallel to one another and each extending from a respective inlet to at least one respective outlet defined in the trailing edge, the at least two internal cooling air passages configured to direct all of the air entering their respective inlets to their respective at least one outlet defined in the trailing edge; and at least one crossover located in the hollow section adjacent to the at least one outlet in the trailing edge, the crossover spaced apart from the trailing edge to define a plenum between the crossover and the at least one outlet in the trailing edge, the crossover generally extending radially in the hollow section and having a distal end portion on an end of the airfoil distally opposite the inlets of the passages, the crossover and the plenum being in fluid communication with the at least two passages one of which said at least two passages being dedicated to supplying cooling air to the distal end portion of the crossover.