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January 24, 2026International Journal of Turbo and Jet Engines

Hybrid thermodynamic and CFD modeling of a UAV-class micro gas turbine engine: performance validation and optimization

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Authors

SCSwati ChauhanGWG. Jims John Wessley

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Overview

This analysis validates performance in UAV-class engines, indicating effective design methodologies for compact propulsion systems.

Key Points

  • The aim is to develop a simulation framework to predict and validate UAV-class micro gas turbine engine performance.
  • Hybrid framework integrating 1D thermodynamic analysis, system-level validation, and 2D CFD simulations.
  • Parametric studies on pressure ratios from 1.3 to 1.5 and Mach numbers between 0.1 and 0.6.
  • Utilization of Gas Turbine Simulation Program (GSP), Flownex, and ANSYS Fluent.
  • CFD predicted nozzle exit velocities exceeding 750 m/s with minimal flow separation.
  • Temperature predictions agreed within 5% across simulation tools.
  • Notable deviations in pressure and mass-flow observed in turbulence-dominated areas.

Cite This Study

Chauhan et al. (2026) studied this question.

synapsesocial.com/papers/6974610cbb9d90c67120aecbhttps://doi.org/10.1515/tjj-2025-0076
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