Bypass line of a premixing burner in gas turbine combustion chambers
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United States of America Patent
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Dec 27, 1994
Grant Date -
N/A
app pub date -
Nov 16, 1993
filing date -
Nov 16, 1992
priority date (Note) -
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Abstract
The present invention pertains to a combustion chamber housing of a gas turbine with a laterally arranged inlet elbow (8) for compressor air, which is uniformly distributed over the perforated cone (9) via an intake heart (6), impacts on the injector tube (10) there, and is deflected in the upward direction in the direction of the flame tube and the burner. It is necessary under certain operating conditions of the gas turbine to regulate the primary air flow to the burner, without having to reduce the output of the upstream compressor. This is accomplished according to the present invention by connecting a bypass line (3) with a compensator (1) and a regulating fixture (2), through which part of the air is sent from the air inlet elbow (8) directly into the interior of the injector tube (10) via an inlet tube (4), to the lower part of the combustion chamber.
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