Combustion instability easily occurs under premixed combustion conditions in gas turbine

and the combustion chamber inlet pressure is known as one of the key factors affecting the combustion stability.In order to study the effects of combustion chamber inlet pressure on premixed combustion stability of gas turbine

the cantype combustor in a heavy duty gas turbine was taken as the research object.Keeping the fuel air equivalence ratio

inlet temperature and flow parameters of the combustion chamber be constant

only change the combustion chamber inlet pressure.The numerical analysis method was applied to calculate the flow field in the combustor

and pressure at different locations of the combustion chamber was monitored for statistical analysis and spectrum analysis.The results show that

there are multiple characteristic frequencies during combustion at different inlet pressures.With an increase in combustion chamber inlet pressure

the pressure pulsation in combustion chamber will be more intense and the main frequency amplitude increases gradually.At the same inlet pressure

the pressure vibration at the combustion chamber monitoring points will be more intense than that in center of the combustion liner.The axial vibration mode is the main vibration mode of combustion oscillation.The results will provide a theoretical foundation for the combustor design modification and the unit safe and stable operation

and provide a more solid basis for further experimental studies.