Bypass and injection method and apparatus for gas turbines
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United States of America Patent
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app pub date -
Jun 8, 2005
filing date -
Sep 16, 2003
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Abandoned
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Abstract
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 radial plane.
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