Patent ID: 8727704

Claim:
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 cooling fluid supply passage within the panel that receives the cooling fluid from the outer side of the panel and delivers the cooling fluid to a first cooling fluid chamber within the panel; at least one serpentine cooling passage that receives the cooling fluid from the first cooling fluid chamber, the cooling fluid providing convective cooling to the panel as it passes through the at least one serpentine cooling passage; a plurality of transitional cooling fluid passages that receive the cooling fluid from the first cooling fluid chamber and discharge the cooling fluid toward the at least one serpentine cooling passage; and at least one cooling fluid discharge passage that discharges the cooling fluid from the cooling system.