Combustor for a gas turbine engine with effusion cooled baffle
AssigneeALSTOM Technology Ltd
InventorMadhavan Narasimhan Poyyapakkam
Life of this patent
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Abstract
A combustor (1) for a gas turbine engine, particularly for a gas turbine having sequential combustion, includes a combustor wall (4) defining a mixing region (5) and a combustion region (6). The mixing region (5) has 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) crosses 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).
Claims9
A combustor for a gas turbine engine, comprising:
- a combustor wall defining a mixing region and a combustion region, the mixing region comprising at least one first inlet for introducing combustion air into the mixing region and at least one second inlet for introducing fuel into the mixing region, the combustion region extending downstream of the mixing region, the mixing region crossing over to the combustion region in a transition region;
- and
- a baffle extending from the transition region generally in the downstream direction, forming at least one space between the combustor wall and the baffle, the baffle comprising holes for effusion cooling of the baffle with air or combustion gas.
Dependencies are inferred from the claim text.