COMBUSTOR FOR GAS TURBINE ENGINE AND GAS TURBINE

摘要

A combustor for gas turbine engine, wherein: a plurality of impingement-cooling holes (39) are opened passing through an external wall (35) of a liner for cooling air (CA) to blow out towards the outer surface of an internal wall (37) of the liner; a plurality of pin-fins (43) are formed on the outer surface of the internal wall (37) of the liner; a plurality of effusion cooling holes (41) are opened passing through the internal wall (37) of the liner for cooling air (CA) to blow out along the inner surface of the internal wall (37) of the liner. The top surface of each pin-fin (43) is not in contact with the inner surface of the external wall (35) of the liner and the ratio (H/D) of the height (H) of the pin-fin (43) to the equivalent diameter (D) of the impingement-cooling hole (39) is set to be 1.0 - 3.0.