A new one-dimensional, time dependent aerothermodynamic mathematical model and computer simulation of the gas turbine engine has been developed. The Aerodynamic Turbine Engine Code (ATEC) simulates the operation of the gas turbine engine by solving conservation equations, expressed as one dimensional, time dependent Euler equations, with turbomachinery source terms. By incorporating both implicit and explicit equation solvers, transient simulations of the gas turbine engine can be conducted efficiently while maintaining the capability of simulating dynamic events such as compressor stall. ATEC can also be used to address dynamic events or steady-state processes to model both on- and off-design engine operation.

A new one-dimensional, time dependent aerothermodynamic mathematical model and computer simulation of the gas turbine engine has been developed. The Aerodynamic Turbine Engine Code (ATEC) simulates the operation of the gas turbine engine by solving conservation equations, expressed as one dimensional, time dependent Euler equations, with turbomachinery source terms. Development of the mathematical models were discussed in Part 1. Part 2 presents the results of exercising the simulation for several different problems. Results are presented for a subsonic, converging / diverging nozzle to demonstrate the validity of the numerical flow solvers and to demonstrate the functionality of the variable time step routine. Gas turbine engine simulation results are presented to demonstrate the capabilities of the ATEC simulation and for calibration purposes. The simulation results were obtained using the operating characteristics of a turboshaft engine.

No abstract

No abstract

No abstract