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Helicopter Turboshaft Engine Database as a Conceptual Design Tool

Journal Article
ISSN: 1946-3936, e-ISSN: 1946-3944
Published June 14, 2021 by SAE International in United States
Helicopter Turboshaft Engine Database as a Conceptual Design Tool
Citation: null
Language: English


Many interconnected parameters are involved in the helicopter turboshaft engine’s design, implying numerous limitations on the design process. These parameters include the key parameters such as weight, dimensions, power, specific fuel consumption, combustion temperature, air mass flow rate, and compressor pressure ratio, all of which correlate with one another and collectively affect the engine’s design process and consequently the helicopter. The first step in any design process is the conceptual design stage, where using an initial guess, an iterative parameter estimation runs until convergence. For the initial guess, a database is required, and for estimation, knowledge of the relationships between different parameters is mandatory. Hence, as an effort to help with this process and given that no publicly available database exists for turboshaft engines, in this work, a unique and comprehensive database of turboshaft engines along with novel insights into useful design parameters and their correlations are presented.