Ring segment with serpentine cooling passages

A ring segment for a gas turbine engine comprising:

• a panel having a leading edge, a trailing edge, a first mating edge, a second mating edge, an outer side, and an inner side, wherein cooling fluid is provided to the outer side and the inner side defines at least a portion of a hot gas flow path through the gas turbine engine;
• a cooling system within the panel that receives cooling fluid from the outer side of the panel for cooling the panel, the cooling system comprising:
• at least one serpentine cooling passage that receives the cooling fluid from the outer side of the panel, the cooling fluid providing convective cooling to the panel as it passes through the at least one serpentine cooling passage, wherein the at least one serpentine cooling passage comprises at least two turns of about 180 degrees, the turns being configured such that the cooling fluid passing through the at least one serpentine cooling passage flows generally axially toward the trailing edge, turns about 180 degrees and flows generally axially toward the leading edge, and again turns about 180 degrees and flows generally axially toward the trailing edge;
• and
• at least one cooling fluid discharge passage that discharges the cooling fluid from the cooling system.