INTERNALLY COOLED AIRFOIL FOR A ROTARY MACHINE

摘要

The invention refers to an internally cooled casted airfoil for a rotary machine, preferably a gas turbine engine comprising a suction and a pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge region of said airfoil. At least one suction wall sided cooling channel extends in axial direction confined by the suction side wall and a first inner wall. At least one pressure wall sided cooling channel extends in axial direction confined by the pressure side wall and a second inner wall. At least one feed chamber is defined between the first and second inner wall for feeding said at least one suction and pressure sided cooling channel each by at least one through hole inside of the first and second inner wall. At least one suction wall sided cooling channel and the at least one pressure wall sided cooling channel extend into the trailing edge region separately. At least one suction wall sided cooling channel and at least one pressure wall sided cooling channel join before discharging at the trailing edge.