The T55-L-712 turboshaft engine, used in the U.S. Army CH-47D Chinook helicopter, has been simulated using version 3.0 of the Advanced Turbine Engine Simulation Technique (ATEST) and version 1.0 of the Aerodynamic Turbine Engine Code (ATEC). The models simulate transient and dynamic engine operation from idle to maximum power and run on an IBM-compatible personal computer. ATEST is a modular one-dimensional component-level transient turbine engine simulation. The simulation is tailored to a specific engine using engine-specific component maps and an engine-specific supervisory subroutine that defines component interrelationships. ATEC is a one-dimensional, time-dependent, dynamic turbine engine simulation. ATEC simulates the operation of a gas turbine by solving the one-dimensional, time dependent Euler equations with turbomachinery source terms. The simulation uses elemental control volumes at the sub-component level (e.g. compressor stage).The paper discusses how limited information from a variety of sources was adapted for use in the T55 simulations and how commonality between the models allowed reuse of the same material. The first application of a new turbine engine model, ATEC, to a specific engine is also discussed. Calibration and operational verification of the simulations will be discussed, along with the status of the simulations.© 1996 ASME

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Application of Transient and Dynamic Simulations to the U.S. Army T55-L-712 Helicopter Engine

Gas Turbine Dynamic Simulation Using Simulink

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Simultaneous multi-design point approach to gas turbine on-design cycle analysis for aircraft engines

The art of engine simulation has come into existence with the advent of analog and digital computers and has become an integral part of any engine development program. It has attracted considerable attention from researchers because of the tremendous bene ts it offers not only in terms of cost reduction, but also because of the con dence it induces into the behavior of gas turbine being designed. A substantial number of works have been carried out in the  eld of engine simulation and its design applicationsduring the past 50 years. The present paper intends to give a comprehensive overview of the attempts that have been made by the earlier researchers, and the considerable amount of knowledge, database, and the expertise that has been made available.

Survey of Advancements in Jet-Engine Thermodynamic Simulation

Modeling and analysis of windmilling operation during mode transition of a turbine-based-combined cycle engine

A generalized turbine engine start simulation (mathematical model) has been developed and demonstrated. The model, designated as ATEST-V3, is capable of simulating engine operation continuously from near static (zero speed) conditions to maximum engine power including windmill starting, spooldown starting, and starterassisted starting. The enhanced capability to simulate the engine starting process provides the means to characterize and understand engine system operational behavior during critical startup and shutdown operations. ATEST-V3 is based on an aerothermodynamic matching of the major components. The component-matching technique is widely used for steady-state and transient turbine engine simulations that typically exclude subidle and starting operations. The same approach is shown to be applicable to engine starting operations by modeling component behavior continuously from zero to maximum power. The combination of an existing transient engine simulation and a numerically stable component-matching algorithm provided a foundation for extending the simulation capability to subidle engine operation and engine starting. ATEST-V3 was applied to a modern flighttype turbofan engine which demonstrated the capability to simulate windmill, spooldown, and starter-assisted starts at various flight conditions. Finally, a comparison is made between model results and engine test data.

M. A. Chappell

Papers

Approach of modeling continuous turbine engine operation from startup to shutdown