Patent ID: 7641440

Claim:
A cooling arrangement for a component, comprising: a component wall comprising first and second layers; the first layer comprising a CMC material comprising a heated front surface and a cooled back surface; the second layer comprising a thermally conductive material disposed on the back surface of the first layer, the thermally conductive material comprising a coefficient of thermal conductivity at least 10 times greater than a corresponding coefficient of thermal conductivity of the CMC material; and a cooling fluid flow that impinges on a cooled back surface of the second layer opposite the first layer; wherein the component is a gas turbine shroud ring segment, the front surface of the first layer is a radially inner surface with respect to an axis of the gas turbine, the second layer comprises a coating on the back surface of the first layer, and further comprising a cooling air injector comprising a plurality of cooling air injection holes that produce a plurality of cooling airflows that impinge against the back surface of the second layer.