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A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body, wherein the combustor body includes a reaction zone for primary combustion of fuel and air, and a casing enclosing the combustor body and defining an annular passageway for carrying com

A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body, wherein the combustor body includes a reaction zone for primary combustion of fuel and air, and a casing enclosing the combustor body and defining an annular passageway for carrying compressor discharge air into the combustor body at one end. The system further may include a reintroduction manifold for receiving combustor bypass air extracted from the compressor discharge air in the annular passageway, and 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. The method may include extracting combustor bypass air from the annular passageway, transporting the combustor bypass air to a reintroduction manifold, and reintroducing the combustor bypass air into the combustor body through one or more reintroduction slots in communication with the reintroduction manifold.

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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 pass

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; andone or more cooling holes for providing cooling air independent of the combustor bypass air to the one or more reintroduction slots. 2. The combustor of claim 1, wherein the one or more cooling holes provides cooling air continuously to the one or more reintroduction slots. 3. The combustor of claim 1, further comprising a valve to regulate the combustor bypass air flowing to the reintroduction manifold. 4. The combustor of claim 1, further comprising an extraction manifold for extracting the combustor bypass air from the annular passageway. 5. The combustor of claim 4, further comprising a conduit for transporting the combustor bypass air from the extraction manifold to the reintroduction manifold. 6. The combustor of claim 1, wherein the one or more reintroduction slots comprise a continuous annular slot in communication with the reintroduction manifold. 7. The combustor of claim 1, wherein the one or more reintroduction slots comprise a plurality of slots in communication with the reintroduction manifold. 8. The combustor of claim 7, wherein the plurality of slots are equally spaced from one another about the combustor body. 9. 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;an extraction manifold for extracting the combustor bypass air from the annular passageway;a reintroduction manifold for receiving the combustor bypass air extracted from the annular passageway;a conduit for transporting the combustor bypass air from the extraction manifold to the reintroduction manifold;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; andone or more cooling holes for providing cooling air independent of the combustor bypass air to the one or more reintroduction slots. 10. The combustor of claim 9, wherein the one or more cooling holes provides cooling air continuously to the one or more reintroduction slots. 11. The combustor of claim 9, wherein the one or more reintroduction slots comprises a continuous annular slot in communication with the reintroduction manifold. 12. The combustor of claim 9, wherein the one or more reintroduction slots comprise a plurality of slots in communication with the reintroduction manifold. 13. The combustor of claim 12, wherein the plurality of slots are equally spaced from one another about the combustor body. 14. A method for bypassing a combustor bypass air around a combustor of a gas turbine, comprising: extracting the combustor bypass air from an annular passageway comprising compressor discharge air, wherein the annular passageway is defined by the space between a combustor body and a casing enclosing the combustor body;transporting the combustor bypass air to a reintroduction manifold;reintroducing the combustor bypass air into the combustor body through one or more reintroduction slots in communication with the reintroduction manifold, wherein the one or more reintroduction slots are downstream of a reaction zone in the combustor body; andproviding cooling air independent of the combustor bypass air to the one or more reintroduction slots through one or more cooling holes. 15. The method of claim 14, wherein transporting the combustor bypass air to a reintroduction manifold comprises transporting the combustor bypass air to the reintroduction manifold through a conduit. 16. The method of claim 14, further comprising regulating the transporting of the combustor bypass air to the reintroduction manifold using a valve. 17. The method of claim 14, wherein the one or more reintroduction slots comprises a continuous annular slot in communication with the reintroduction manifold. 18. The method of claim 14, wherein the one or more reintroduction slots comprises a plurality of slots in communication with the reintroduction manifold. 19. The method of claim 18, wherein the plurality of slots are equally spaced from one another about the combustor body.