Ring segment with forked 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, 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 supply portion including a transition section that extends generally axially toward the leading edge of the panel;
• a generally axially extending portion located downstream from the supply portion with respect to a flow of cooling fluid through the cooling fluid passage, the axially extending portion located circumferentially adjacent to the supply portion and extending generally axially toward the trailing edge of the panel generally parallel to the transition section;
• and
• at least one fork downstream from the axially extending portion with respect to the flow of cooling fluid through the cooling fluid passage, the at least one fork dividing each cooling fluid passage into at least two downstream portions.