| 摘要 |
<p>A gas turbine engine annular combustor (18) having a bulkhead (19) at its upstream end 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 (38) in the bulkhead (19) direct cooling air into the chambers (31). Further apertures (50) in the heat shields (28) exhaust the cooling air in a common circumferential direction so that the air flows merge to define a substantially continuous annular flow of cooling air about the longitudinal axis of the combustor (18) and across the downstream heat shield faces. <IMAGE></p> |
