초록 ▼

A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold.

A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold. A conduit feeds the extracted air into an injection manifold having a plurality of injection tubes for injecting the extracted air into the combustor bypassing the reactor. The injection tubes and the injection manifold are disposed in a substantially common axial plane.

대표청구항 ▼

1. A combustor for a gas turbine, comprising: a combustor body; a casing enclosing said combustor body and defining an annular passageway therebetween for carrying compressor discharge air into said combustor body at one end thereof; a reaction zone within said combustor body for main combustio

1. A combustor for a gas turbine, comprising: a combustor body; a casing enclosing said combustor body and defining an annular passageway therebetween for carrying compressor discharge air into said combustor body at one end thereof; a reaction zone within said combustor body for main combustion of fuel and air; a first annular manifold surrounding said casing and arranged to extract a predetermined amount of compressor discharge air from said annular passageway; a second annular manifold surrounding said casing manifold and arranged to receive the extracted air, said second manifold located downstream of said first manifold in a combustion flow direction; a conduit for supplying the extracted air from said first manifold to said second manifold; and a plurality of injection tubes in communication with said second manifold for injecting the extracted air into said combustor body downstream of said reaction zone in the combustion flow direction to quench combustion, said injection tubes and said second manifold being disposed in a substantially common radial plane. 2. The combustor of claim 1, further comprising: an array of openings disposed in said casing to permit the compressor discharge air to flow through said openings into said first manifold; and a conduit for supplying the extracted air from said first manifold to said second manifold. 3. The combustor of claim 2, wherein said second manifold includes an access flange for each injection tube. 4. The combustor of claim 3, wherein the injection tubes are equally spaced from one another about said second manifold. 5. The combustor of claim 1, wherein said conduit includes a control valve to regulate air flowing from said first manifold to said second manifold. 6. A gas turbine comprising: a compressor section for pressurizing air; a combustor for receiving the pressurized air; and turbine section for receiving hot gases of combustion from the combustor, said combustor including a combustor body with an inner liner, a casing enclosing said body and defining a passageway therebetween for carrying compressor discharge air, a reaction zone within said combustor body for combustion of fuel and air, a first manifold surrounding said casing and arranged to extract a predetermined amount of compressor discharge air from said passageway, a second manifold surrounding said casing and arranged to receive the extracted air, said second manifold located downstream of said first manifold in a combustion flow direction; a conduit for supplying the extracted air from said first manifold to said second manifold, and a plurality of injection tubes in communication with said second manifold for injecting the extracted air into said combustor body downstream of said reaction zone in the combustion flow direction to quench combustion, said injection tubes and said second manifold being disposed in a substantially common radial plane. 7. A gas turbine according to claim 6, wherein said casing further includes an array of openings adjacent to said first manifold to enable the compressor discharge air to flow through said openings into said first manifold. 8. The gas turbine of claim 7, wherein said second manifold includes an access flange for each injection tube. 9. The gas turbine of claim 8, wherein the injection tubes are equally spaced from one another about said second manifold.