Airfoil trailing edge cooling arrangement.

摘要

57 A turbine airfoil for high temperature applications has a spanwise trailing edge slot (54) and a cut back pressure side wall (22). The pressure side wall (22) has a thickness t at its downstream end. The slot (54) is divided into channels (56) which discharge a film of cooling air over the exposed back surface (65) of the suction side wall (24) downstream of the cut back pressure side wall (22). Each channel (56) tapers from a throat at its upstream end (which meters the flow of cooling air) to the slot outlet of width s. The airfoil (12) is designed with a ratio t/s of no more than 0.7 which significantly improves cooling of the trailing edge (61), reduces required cooling air flow, and permits greater cut back distances. Figs 3 + 4