SYSTEM AND METHOD FOR REINTRODUCING COMBUSTION BYPASS FLOW OF GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To reintroduce a combustion bypass flow of a gas turbine. SOLUTION: A combustor body (11) includes a reaction area (15) for primary combustion of fuel and air and a casing (12) surrounding the combustor body (11) and defining an annular passage (13) for carrying compressor delivery air to one end (14) of the combustor body (11). The system can also include a reintroducing manifold (19) for receiving combustor bypass air extracted from the compressor delivery air in the annular passage (13) and one or a plurality of reintroducing slots (21) communicating with the reintroducing manifold (19) so as to inject the combustor bypass air into the combustor body (11) on the downstream side of the reaction area (15). COPYRIGHT: (C)2011,JPO&INPIT