On design of new generation start-up system for aero gas turbine engines
In order to ensure the possibility of the aero engine start-up over the flight envelope and to reduce maintenance costs, a concept of intelligent start-up system is proposed using additional factors (controlled ignition devices, variable geometry, air take out, turbocompressor power, inlet and outlet devices, etc.) and the development of the system for programmed start-up control of the combustion chamber: ignition energy, air in-flow parameters in the combustion chamber, fuel flow with dynamical adjustment of the combustion chamber sensitivity. The proposed design and refining technology of the intelligent start-up system is based on the experience of mathematical modelling and simulation of start-up of a variety of gas turbine engines.