Method for operating a micro turbine assembly, in which fuel in the form of fuel gas is supplied to a combustion chamber system via a fuel supply line, wherein - the fuel flow upstream of the combustion chamber system is compressed to a supply pressure by means of a compressor device (14, 14') of a compressor unit (12, 12') and, downstream of the compressor unit (12, 12'), is allocated in a burner-specific portion (20, 20') to two line portions (21, 21', 22, 22') for the separate fuel supply of a main stage and a pilot stage of the combustion chamber system and, after allocation, the fuel flows through at least one cross-sectional reduction means (210, 411) arranged in the burner-specific portion (20, 20'), - the fuel flow is controlled or regulated via the line portion (22, 22') of the pilot stage by means of the at least one cross-sectional reduction means on the basis of the fuel flow via the line portion (21, 21') of the main stage, - the fuel flow is controlled or regulated via the line portion (22, 22') of the pilot stage on the basis of a predetermined ratio to the fuel flow via the line section of the main stage, and wherein - for controlling or regulating the fuel flow, the ratio of the fuel flow of the pilot stage to the fuel flow of the main stage is determined in a determination unit (53, 53') at least on the basis of a turbine outlet temperature downstream of a turbine assembly (60, 60') of the micro turbine assembly and a turbine speed of the turbine assembly (60, 60'), and an open position of the cross-sectional reduction means is subsequently determined in the determination unit (53, 53') taking the ratio into account, and is specified to the cross-sectional reduction means. - the fuel flow upstream of the combustion chamber system is compressed to a supply pressure by means of a compressor device (14, 14') of a compressor unit (12, 12') and, downstream of the compressor unit (12, 12'), is allocated in a burner-specific portion (20, 20') to two line portions (21, 21', 22, 22') for the separate fuel supply of a main stage and a pilot stage of the combustion chamber system and, after allocation, the fuel flows through at least one cross-sectional reduction means (210, 411) arranged in the burner-specific portion (20, 20'), - the fuel flow is controlled or regulated via the line portion (22, 22') of the pilot stage by means of the at least one cross-sectional reduction means on the basis of the fuel flow via the line portion (21, 21') of the main stage, - the fuel flow is controlled or regulated via the line portion (22, 22') of the pilot stage on the basis of a predetermined ratio to the fuel flow via the line section of the main stage, and wherein - for controlling or regulating the fuel flow, the ratio of the fuel flow of the pilot stage to the fuel flow of the main stage is determined in a determination unit (53, 53') at least on the basis of a turbine outlet temperature downstream of a turbine assembly (60, 60') of the micro turbine assembly and a turbine speed of the turbine assembly (60, 60'), and an open position of the cross-sectional reduction means is subsequently determined in the determination unit (53, 53') taking the ratio into account, and is specified to the cross-sectional reduction means.