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A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas t

A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend 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. 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.

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1. 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 sour

1. 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; andthe 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. 2. The ring segment of claim 1, wherein the impingement holes are aligned with the flow channels such that impingement cooling air is directed to portions of the outer side of the inner panel that define the flow channels. 3. The ring segment of claim 2, wherein the inner side of the outer panel is in engagement with and bonded to the outer side of the inner panel along portions of the inner panel surrounding the flow channels. 4. The ring segment of claim 3, wherein the outer panel is bonded to the inner panel with a diffusion bond. 5. The ring segment of claim 2, wherein the impingement holes direct cooling air from the supply of cooling air to impinge on the outer side of the inner panel at intersections formed by the flow channel grid pattern. 6. The ring segment of claim 1, wherein the flow channels are formed by grooved portions in the outer side of the inner panel. 7. The ring segment of claim 6, wherein the impingement holes direct cooling air from the supply of cooling air to impinge on the outer side of the inner panel at the intersections formed by the flow channel grid pattern. 8. The ring segment of claim 6, wherein the flow channels include axial flow channels extending from the leading edge to the trailing edge and circumferential flow channels extending from the first mating edge to the second mating edge. 9. The ring segment of claim 8, including axial exit openings at the ends of the axial flow channels at the leading and trailing edges, and circumferential exit openings at the ends of the circumferential flow channels at the first and second mating edges, wherein cooling air entering the ring segment through the impingement holes exits the ring segment through the axial and circumferential exit openings. 10. The ring segment of claim 1, including hook members rigidly attached to the outer panel for supporting the ring segment to an outer casing of a turbine engine. 11. 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; andthe 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 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. 12. The ring segment of claim 11, wherein the impingement holes direct cooling air from the supply of cooling air to impinge on the outer side of the inner panel at intersections formed by the flow channel grid pattern. 13. The ring segment of claim 12, wherein the inner side of the outer panel is in engagement with and bonded to the outer side of the inner panel along portions of the inner panel in between adjacent ones of the flow channels. 14. The ring segment of claim 13, wherein the outer panel is bonded to the inner panel with a diffusion bond. 15. The ring segment of claim 12, wherein the axially and circumferentially extending flow channels are formed by grooved portions in the outer side of the inner panel. 16. The ring segment of claim 12, wherein the axial flow channels extend from the leading edge to the trailing edge and the circumferential flow channels extend from the first mating edge to the second mating edge. 17. The ring segment of claim 16, including axial exit openings at the ends of the axial flow channels at the leading and trailing edges, and circumferential exit openings at the ends of the circumferential flow channels at the first and second mating edges, wherein cooling air entering the ring segment through the impingement holes exits the ring segment through the axial and circumferential exit openings. 18. The ring segment of claim 12, including hook members rigidly attached to the outer panel for supporting the ring segment to an outer casing of a turbine engine.