Abstract: Methods and systems are provided for automated tuning of gas turbines and other combustion systems. In certain examples, a gas turbine combustion system may include a tuning controller including non-transitory memory and executable instructions, stored in the non-transitory memory, that, if executed by a processor, cause the tuning controller to: receive one or more operational parameters; and cause one or more operational control elements, that are to control one or more actuatable components of the gas turbine combustion system, to be proportionally adjusted based at least in part, on a magnitude of an error of the one or more operational parameters relative to a threshold.