Patent ID: 8281601
Filing Date: 2012-10-09
Classification: F23R

Abstract:
1. A combustor for a gas turbine configured for reintroducing a combustor bypass air extracted from a compressor discharge air, comprising: a combustor body, wherein the combustor body comprises a reaction zone for primary combustion; a casing enclosing the combustor body and defining an annular passageway therebetween for carrying the compressor discharge air into the combustor body at one end thereof; a reintroduction manifold for receiving the combustor bypass air extracted from the compressor discharge air in the annular passageway; one or more reintroduction slots in communication with the reintroduction manifold for injecting the combustor bypass air into the combustor body downstream of the reaction zone; and one or more cooling holes for providing cooling air independent of the combustor bypass air to the one or more reintroduction slots.