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ATEC: The Aerodynamic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations: Part 2 — Numerical Simulations FREE

[+] Author Affiliations
Doug Garrard

Sverdrup Technology Inc., Arnold AFB, TN

Paper No. 96-GT-194, pp. V005T16A007; 8 pages
doi:10.1115/96-GT-194
From:
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; General
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7876-7
  • Copyright © 1996 by ASME

abstract

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.

Copyright © 1996 by ASME
This article is only available in the PDF format.

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