The suppression of combustion instabilities using the extremum seeking algorithm(ESA) is analyzed.A function model of the pressure oscillation and the mean fuel–air ratio in the combustion chamber is derived and impl...The suppression of combustion instabilities using the extremum seeking algorithm(ESA) is analyzed.A function model of the pressure oscillation and the mean fuel–air ratio in the combustion chamber is derived and implies an extremum relation between the oscillation amplitude of the pressure and the mean fuel–air ratio.Hence, the control system of combustion instabilities can be considered as an extremum seeking control system(ESCS). All traditional ESCSs employ a separate design method, which divides the design of the ESA from the controller design. It is thus difficult for traditional ESCSs to achieve optimal performance of the control system. To solve this problem, an integrated extremum seeking control method for ESCSs is proposed. Using this integrated control, the minimal oscillation amplitude of the pressure is realized by adaptively seeking the optimal mean fuel–air ratio. Hence, this design method can effectively suppress combustion instabilities in aeroengines. By comparing simulation results, the effectiveness of the proposed method is validated.展开更多
基金supported by the National Natural Science Foundation of China(60674090)
文摘The suppression of combustion instabilities using the extremum seeking algorithm(ESA) is analyzed.A function model of the pressure oscillation and the mean fuel–air ratio in the combustion chamber is derived and implies an extremum relation between the oscillation amplitude of the pressure and the mean fuel–air ratio.Hence, the control system of combustion instabilities can be considered as an extremum seeking control system(ESCS). All traditional ESCSs employ a separate design method, which divides the design of the ESA from the controller design. It is thus difficult for traditional ESCSs to achieve optimal performance of the control system. To solve this problem, an integrated extremum seeking control method for ESCSs is proposed. Using this integrated control, the minimal oscillation amplitude of the pressure is realized by adaptively seeking the optimal mean fuel–air ratio. Hence, this design method can effectively suppress combustion instabilities in aeroengines. By comparing simulation results, the effectiveness of the proposed method is validated.
