Aeroengine transient performance simulation integrated with generic heat soakage and tip clearance model

Abstract The simulations and assessment of transient performance gas turbine engines during the conceptual preliminary design stage may be conducted ignoring heat soakage tip clearance variations due to lack detailed geometrical structural information. As a result, problems with stability not revealed correctly, corresponding iterations would necessary costly when those are at stage. To make an engine more cost time effective, it has become important require better considering all key impact factors such as fuel control schedule, rotor dynamics, inter-component volume effect well variation effects. In this research, novel simulation approach generically simplified models for major path components including compressors, turbines combustors been developed support realistic stages. Such only thermodynamic parameters input, which is normally available have implemented into in-house software applied model twin-spool turbojet test their effectiveness. Comparisons between simulated without effects demonstrate that results promising. Although introduced accurate using component information, able include analysis