Patent ID: 8894352

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, and wherein an axial direction is defined between the leading and trailing edges and a radial direction is defined between the outer and inner sides; and 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: a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel, the cooling fluid passages each comprising a generally axially extending portion extending through the panel in the axial direction and including at least one fork, the at least one fork dividing each cooling fluid passage into at least two downstream portions that each receive cooling fluid from the respective axially extending portion.