FIELD: gas industry.
SUBSTANCE: invention relates to a gas turbine installation. The gas turbine installation contains a compressor, an injection chamber connected to the compressor, a combustion chamber with a combustion device, containing a front panel, at least a damper connected to the front panel and located in the injection chamber, and burners connected to the front panel, while the front panel and burners are at least partially located in the injection chamber, while the damper has a chamber adapted to a space available between adjacent burners. The damper is Helmholtz damper and contains a chamber and a neck, while the neck connects the chamber to the front panel.
EFFECT: invention allows for prevention of mechanical destruction of components of a combustion chamber.
12 cl, 13 dwg
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