A New Scaling Method for Component Maps of Gas Turbine Using System Identification

Abstract

A scaling method for characteristics of gas turbine components using experimental data or partially given data from engine manufacturers was newly proposed. In case of currently used traditional scaling methods, the predicted performance around the on-design point may be well agreed with the real engine performance, but the simulated performance at off-design points far away from the on-design point may not be well agreed with the real engine performance generally. It would be caused that component scaling factors, which were obtained at on-design point, is also used at all other operating points and components’ maps are derived from different known engine components. Therefore to minimize the analyzed performance error in the this study, first components’ maps are constructed by identifying performances given by engine manufacturers at some operating conditions, then the simulated performance using the identified maps is compared with performances using currently used scaling methods. In comparison, the analyzed performance by the currently used traditional scaling method was well agreed with the real engine performance at on-design point but had maximum 22% error at off design points within the flight envelope of a study turboprop engine. However, the performance result by the newly proposed scaling method in this study had maximum 6% reasonable error even at all flight envelope.