Methods and systems for cooling gas turbine engine airfoils

摘要

A gas turbine engine includes rotor blades including airfoils (42) that facilitates reducing manufacturing losses due to airfoil trailing edge (50) scarfing. Each airfoil includes a first and second sidewall (44, 46) connected at a leading edge (48) and a trailing edge (50). The sidewalls define a cooling cavity (70) that includes at least a leading edge chamber (80) bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber (82) bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region (102), a throat (108), and a passageway region (100) connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip (54) and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.