Volume 2 - Issue 4, July - August 2026

This paper presents a zero-dimensional thermo-gasdynamic model for simulating the steady-state and transient response of the PT6A turboprop engine when operating with Jet A-1, TS-1, and assumed blends of these two fuels. The model is updated according to a compressor configuration consisting of four axial-compressor stages and one centrifugal-compressor stage. The conservation equations of mass, energy, and angular momentum are applied to individual engine components, including the inlet, compressor assembly, combustor, compressor turbine, and free turbine. The lower heating value of the fuel is introduced directly into the combustor energy-balance equation to investigate the influence of fuel variation on the combustor-exit temperature, compressor pressure ratio, compressor outlet pressure, propeller speed, and propeller-shaft power. Reduced simulation results for five fuel cases, ranging from 100% Jet A-1 to 100% TS-1, show that the thermodynamic differences are small because both fuels belong to the kerosene family and have similar lower heating values. As the TS-1 fraction increases from 0% to 100%, the peak T3 temperature decreases from 1239.52 K to 1234.70 K, the compressor outlet pressure decreases from 787.16 kPa to 785.41 kPa, and the propeller-shaft power decreases from 562.24 kW to 560.27 kW. All cases maintain the peak T3 temperature below the 1300 K limit in the current model. The results indicate that TS-1 can be evaluated as an alternative fuel with a limited influence on the system-level response of the PT6A engine; however, the final quantitative conclusion must be verified using experimental data and actual fuel properties for each fuel batch.

Phan Le, Mai Vinh Long,"Thermo-Gasdynamic Modeling and Transient-Response Analysis Of The Pt6A Engine Operating With Jet A-1 And TS-1" International Journal of Advanced Multidisciplinary Research and Educational Development, V2(4): Page(40-45) July - August 2026. ISSN: 3107-6513. www.ijamred.com. Published by Scientific and Academic Research Publishing.