| 摘要 |
<p>A gas turbine engine combustor (20) is provided with a wall structure (22) which comprises an outer wall (24) having a plurality of wall elements (26) attached thereto. Each wall element (26) is provided with a flange (27) around its periphery which serves to define a chamber (28) between each wall element (26) and the outer wall (24). Holes (30) in the outer wall (24) permit the flow of cooling air into each chamber (28) to provide impingement cooling of the wall elements (26). Holes (30) in the wall elements (26) permit the exhaustion of cooling air from the chambers (28) to provide film cooling of the wall elements (26).</p> |
