FIELD: engines and pumps.
SUBSTANCE: invention relates to gas turbines. Gas turbine combustion device comprises air intake, first measuring device to measure amount of gas in air intake, at least one combustion chamber and multiple lines to feed fuel into combustion chamber. It comprises exhaust pipe, second measuring device to measure amount of gas in air intake and control device to vary fuel feed fuel into multiple lines and to control gas amount in exhaust pipe. Note here that said variation is executed subject to both gas amount in air intake and gas amount in exhaust pipe.
EFFECT: higher reliability and efficiency.
16 cl, 8 dwg
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