FIELD: engines and pumps.
SUBSTANCE: gas turbine has gas duct to direct gas flow and some combustion chambers. Note here that each combustion chamber leads into gas duct and comprises gas burner. Proposed method comprises the following stages: measuring first temperature in preset time in, at least, every two points located downstream of combustion chambers in gas duct, measuring second temperature in preset time in two burners, and detecting partial tail coil extinction from measured first and second temperatures. Note here that detecting of partial tail coil extinction comrises the stage of determining the first detecting parameter. This first detecting parameter is measured using the speed of modification first temperatures in different points of measuring.
EFFECT: higher reliability and efficiency.
10 cl, 3 dwg
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