The invention relates to a gas turbine (100) and suitable operating methods, wherein the gas turbine (100) comprises a compressor (1) for providing compressed air (2), a combustion chamber (4) provided with a burner (3), and an expansion turbine (5), wherein a bypass flow channel (10) is also provided which is designed to supply compressed air (2) past the burner (3) and to supply a hot gas flow (6) generated in the combustion chamber (4) during operation of the gas turbine (100), and wherein in addition the opening cross section (Q) of the bypass flow channel (10) can be adjusted by adjusting means (11), and wherein in addition an adjustment unit (20) is comprised, which is designed to adjust the opening cross section (Q) of the bypass flow channel (10) in such a way that the modification speed of the opening cross section (Q) is selected in such a way that the relative combustion chamber pressure drop (DeltaBDV) or a material temperature (MT) of the combustion chamber (4) is substantially constant, in particular that the relative combustion chamber pressure drop (DeltaBDV)) or the material temperature (MT) of the combustion chamber does not vary by more than 10%.