Gas turbine assembly and corresponding operating method
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United States of America Patent
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Sep 15, 2020
Grant Date -
Feb 6, 2014
app pub date -
Oct 8, 2013
filing date -
Apr 8, 2011
priority date (Note) -
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Abstract
The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.
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