To carry out calculation of specified engine performance quickly

general aeroengine performance simulation system was built based on object-oriented technique. At the same time

a variable component method of gas thermodynamic properties for calculation was adopted to overcome the defects in the current calculation model. In the performance simulation of engine

coupling

bleeding

cooling and power extraction were considered. Moreover

debug can be achieved easily and correctly because some exception handling facilities were added into it. Thus

reliability of system was improved. A simulation of two-spool mixed turbofan engine was performed

and the results were compared with experimental data. The results show that the variable component method has good accuracy. The error of thrust is usually less than 3%

and that of specific fuel consumption is less than 2.5%. Besides the precision has improved especially at high altitude and low Mach number.