Gas turbine combustion chamber arrangement of axial type of construction
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United States of America Patent
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Oct 6, 2015
Grant Date -
Apr 11, 2013
app pub date -
Jun 15, 2011
filing date -
Jun 15, 2010
priority date (Note) -
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Abstract
A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annular guide vane area in which guide vanes are arranged, which for redirecting an incoming flow are provided at an angle (α) in a range between 28° and 32° relative to a central axis of the gas turbine. Downstream of the guide vane area, a diffuser area is arranged, the diffuser area not being provided with flow-guiding elements affecting the flow, where burners arranged in the annular combustion chamber are provided with their burner axes at an angle (β) between 40° and 50° relative to the central axis.
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