ATEC: The Aerodyanmic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations

A new one-dimensional, time dependent aerothermodynamic mathematical model and computer simulation of the gas turbine engine has been developed and is introduced herein. The Aerodynamic Turbine Engine Code (A TEC) 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 onand off-design engine operation. The dissertation is presented in seven chapters. The first chapter introduces the gas turbine engine and discusses its operation. Out of this discussion falls the reason for striving for a mathematical model and computer simulation of the gas turbine engine. Previous efforts at providing a mathematical model and computer simulation of the gas turbine engine are summarized in the second chapter, with particular focus given to their contribution to the advancement of the state-of-the-art in gas turbine engine modeling. It is shown that the current state-of-the-art is advanced by the development of the A TEC model and simulation. The third chapter of the dissertation provides an overview of the mathematical approach taken within A TEC. The general philosophy of the A TEC mathematical model is discussed, and the method of solving the governing equations using both an explicit and implicit equation solver is presented. The third chapter of the

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