Cooling system including wavy cooling chamber in a trailing edge portion of an airfoil assembly

An airfoil assembly in a gas turbine engine comprising:

• a platform assembly;
• and
• an airfoil comprising:
• an outer wall coupled to the platform assembly and comprising a leading edge portion including a leading edge, a trailing edge portion including a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined between the leading and trailing edges and a radial direction is defined between the radially inner and outer ends;
• a cooling fluid cavity defined in the outer wall, the cooling fluid cavity receiving cooling fluid from the platform assembly for cooling the outer wall;
• and
• a cooling system that receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall, the cooling system comprising:
• a plurality of radially spaced-apart first impingement channels extending generally in the chordal direction from the cooling fluid cavity to a first cooling fluid chamber for delivering cooling fluid from the cooling fluid cavity to the first cooling fluid chamber, the first cooling fluid chamber having a direction of elongation in the radial direction;
• a plurality of radially spaced-apart second impingement channels extending generally in the chordal direction from the first cooling fluid chamber to a second cooling fluid chamber for delivering cooling fluid from the first cooling fluid chamber to the second cooling fluid chamber, the second cooling fluid chamber having a direction of elongation in the radial direction;
• a plurality of radially spaced-apart third impingement channels extending generally in the chordal direction from the second cooling fluid chamber to a third cooling fluid chamber for delivering cooling fluid from the second cooling fluid chamber to the third cooling fluid chamber, the third cooling fluid chamber having a direction of elongation in the radial direction and being defined by opposing first and second sidewalls comprising respective alternating angled sections that provide the third cooling fluid chamber with a zigzag shape when viewed from a radially outer side of the cooling system;
• a plurality of outlet passages extending from the third cooling fluid chamber to the trailing edge of the outer wall, the outlet passages receiving cooling fluid from the third cooling fluid chamber and discharging the cooling fluid from the airfoil;
• and a plurality of turbulating features provided within the third cooling fluid chamber, the turbulating features effecting a turbulated flow of cooling fluid through the third cooling fluid chamber, wherein the turbulating features are formed in the first and second sidewalls such that a chordal spacing between adjacent turbulating features is substantially equal to or less than a chordal width of the turbulating features.