Combustor for a gas turbine engine

摘要

The invention relates to a combustor (1) for a gas turbine engine, particularly for a gas turbine having sequential combustion. The combustor (1) comprises a combustor wall (4) defining a mixing region (5) and a combustion region (6). The mixing region (5) comprises at least one first inlet (2) for introducing combustion air into the mixing region (5) and at least one second inlet for introducing fuel into the mixing region (5), the combustion region (6) extending downstream of the mixing region. The mixing region (5) crossing over to the combustion region (6) in a transition region (14).
A baffle (9) extends from the transition region (14) generally in the downstream direction (15) forming at least one space (10) between the combustor wall (4) and the baffle (9).