Patent ID: 8684662

Claim:
A ring segment for a gas turbine engine comprising: an outer panel defining a structural body for the ring segment, the outer panel having a leading edge, a trailing edge, a first mating edge, a second mating edge, an outer side and an inner side, the outer side being in communication with a source of cooling air; an inner panel including an outer side and an inner side wherein the outer side of the inner panel is attached to the inner side of the outer panel at an interface, the inner panel defining at least a portion of a hot gas flow path through a gas turbine engine; a plurality of impingement holes extending through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel, wherein the impingement holes are arranged in an impingement hole grid pattern; and the outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels wherein the flow channels intersect to form a flow channel grid pattern and wherein the impingement hole grid pattern corresponds to the flow channel grid pattern.