Comprehensive Analysis of Turboprop Engine Performance Under Diverse Flight Conditions with Pressure Ratio as an Efficiency Parameter Utilizing the Digital Twin Methodology
Year: 2026
Type: preprint
Abstract: Traditional mechanical dynamic models and empirical testing methods present inherent limitations in the performance analysis of turboprop engines, particularly regarding scalability, real-time data integration, and high-fidelity three-dimensional modeling. To overcome these constraints, this study presents a comprehensive diagnostic analysis focused on compressor pressure ratio optimization utilizing a digital twin (DT) methodology. The research aims to enhance the multi-objective efficiency of turboprop engines, with a specific focus on short-haul aviation profiles. By utilizing the digital twin paradigm, compressor and turbine performance maps were dynamically characterized to evaluate the coupled effects of operating speed, mass flow rate, and isentropic efficiency under diverse operational envelopes. The developed virtual model enables the high-fidelity simulation of real-time pressure ratio fluctuations across variable flight scenarios and ambient environmental gradients, including altitude, atmospheric temperature, and pressure. Validated under rigorous flight conditions, the empirical findings underscore the critical role of the pressure ratio in maximizing engine efficiency and demonstrate that its optimal values can be precisely determined through this advanced prognostic framework. In contrast to conventional, static approaches, this study provides a highly adaptable and sensitive methodology for evaluating propulsion performance during dynamic flight phases. Ultimately, this research offers a valuable contribution to enhancing the thermal and propulsive efficiency of turboprop configurations while establishing a scalable design framework for next-generation aerospace propulsion systems.
Source: Research Square
Institutions: Erciyes University, Vilnius Gediminas Technical University
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W7204170645