Ring segment with impingement and convective cooling

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;
• and
• the outer and inner panels define a plurality of axially extending flow channels and a plurality of circumferentially extending flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels.