GAS TURBINE AIRFOIL WITH SHAPED TRAILING EDGE COOLANT EJECTION HOLES

摘要

The invention relates to a turbine airfoil, i.e. blade (5) or vane, with at least one internal radial channel (1-4) for the circulation of cooling medium (13-18) bordered on a pressure side (8) by a pressure side wall and on a suction side (9) by a suction side wall joined at a upstream side at a leading edge (6) and at and downstream side at the trailing edge (7), wherein the turbine blade (5) or vane comprises at least one exit hole (11, 12, 22) through at least one of pressure side wall or suction side wall for the blowing out of cooling medium (13-18) from the internal radial channel (1-4) to the medium surrounding the blade (5) or vane. In accordance with the invention, airfoil is characterised in that along the trailing edge (7) there is at least one trailing edge exit hole (22) the surfacial exit opening of which is located at the pressure side (8) of the trailing edge (7). The invention furthermore pertains to turbines equipped with such airfoils.