| 摘要 |
<p>A gas turbine engine annular combustor (18) having a bulkhead (19) at its upstream which is thermally protected by an annular array of heat shields (28). Each heat shield (28) is provided with integral flanges (32) which space apart the heat shields (28) and bulkhead (19) to define chambers (31) therebetween. Apertures (39) in the bulkhead (19) direct cooling air into the chambers (31) at positions adjacent the outer peripheries of the heat shields (28). The cooling air flows generally inwards within each chamber (31) before being exhausted therefrom. <IMAGE></p> |
