US Patent 10393029 Setting control for gas turbine engine component(s)

A method of controlling settings of one or more actuatable gas turbine engine components includes: providing a first matrix which relates reduction in the operational parameter maximum value during the transient manoeuvre to settings of the component(s); providing a second matrix which relates the operational parameter maximum values attained during the transient manoeuvre: time to attain the maximum value after transient manoeuvre initiation, and operational parameter rate of change at the time of the maximum value; monitoring the engine in operation to identify a start of a transient manoeuvre; predicting, on the basis of the second matrix maximum values, an overshoot operational parameter amount during the identified transient manoeuvre and a time the overshoot occurrence; selecting a setting, using the first matrix, to eliminate the predicted overshoot; and applying the setting to the component(s) for a predetermined period around the predicted time of occurrence to reduce or avoid the overshoot.