Design and Analysis of Boosted Turboshaft Using GasTurb 14: A Study on Thermodynamic Performance and Cooling Systems

Abstract

efficiency and performance are significantly influenced by thermodynamic design, including the compressor, combustion chamber, and turbine. This study aims to design and analyze a gas turbine system with a Boosted Turboshaft configuration using GasTurb 14 software. The design parameters considered include compressor pressure ratio, airflow mass, combustion efficiency, fuel calorific value, and turbine cooling system. These input parameters were processed to simulate system performance through three primary diagrams: Temperature-Entropy (T-s), Enthalpy-Entropy (h-s), and Pressure-Volume (P-v). The simulation results demonstrate that a high-pressure ratio in the compressor improves thermodynamic efficiency, while the optimal combustion temperature in the combustion chamber reaches approximately 1500 K. The expansion process in the turbine results in significant pressure and temperature drops, reflecting efficient conversion of thermal energy into mechanical energy. The cooling system was also analyzed, with 4% airflow allocated for High-Pressure Turbine (HPT) cooling and 6% for Nozzle Guide Vane (NGV) cooling, ensuring the thermal integrity of the turbine blades. Pressure leaks, such as an HP leak to LPT exit of 1%, were also accounted for to identify irreversibility within the system. This study introduces novelty in cooling system management and bleed air analysis, which are rarely highlighted in previous studies. GasTurb 14-based simulations enable detailed analysis of gas turbine designs, relevant for modern propulsion and energy generation applications. The findings are expected to contribute to the development of more efficient and reliable gas turbine technologies.