| 摘要 |
A wall arrangement 310 for the main gas path of a gas turbine engine comprises a wall segment 312 which defines the main gas path, the wall segment having a gas path side 320, an outboard side 322 and a support wall 324 extending from the outboard side towards a supporting structure. A channel member 350 abuts the support wall and defines one or more channels 356 between the support wall and channel member. The channel has radially separated inlet 352 and outlet 354, so that radial cooling flow is provided. This cooling arrangement may be particularly useful for a ceramic composite (CMC) component. |
