Gas turbine combustor including burner having plural gaseous fuel manifolds
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United States of America Patent
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May 16, 2017
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N/A
app pub date -
Nov 15, 2013
filing date -
Nov 26, 2012
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Abstract
A gas turbine combustor includes: multiple gaseous fuel nozzles to inject gaseous fuel; a manifold to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange to secure a burner to an end cover; and a burner body to connect the manifold and the burner flange. Gaseous fuel passages are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold.
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