Gas turbine centripetal annular combustion chamber and method for flow guidance
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United States of America Patent
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Oct 6, 2015
Grant Date -
Jun 5, 2014
app pub date -
Jun 14, 2012
filing date -
Jul 28, 2011
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Abstract
A gas-turbine combustion chamber arrangement includes at least one centrifugal compressor as well as one centripetal annular combustion chamber, with a stator vane arrangement being provided between the centrifugal compressor and the annular combustion chamber. The stator vane arrangement for diverting the air flowing out of the centrifugal compressor is designed at an angle α of 20° to 30°, preferably 25°, relative to the engine axis, so the airflow is passed at essentially this angle α to the combustion chamber. The inflow area into the combustion chamber for supplying air is designed at an angle of 20° to 30°, preferably 25°, relative to the meridional plane, and the center axes of the burners or of the injection nozzles of the combustion chamber are arranged inclined at an angle β of 30° to 40°, preferably 35°, relative to a meridional plane passing through the engine axis.
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