This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.
- International Gas Turbine Institute
Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure
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Tsujikawa, Y, & Nagaoka, M. "Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure." Proceedings of the ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery. Brussels, Belgium. June 11–14, 1990. V002T02A001. ASME. https://doi.org/10.1115/90-GT-115
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