Pignatelli F., Subash A.A., Richter M., Sanned D. & Fureby C.; 2024, “Experimental and Numerical Investigation of Sustainable Aviation Fuels on a Helicopter Combustion Chamber”, ISABE-2024-174, ISABE, Toulouse, France, 22-27 Sept. (https://www.isabe.org/#)
Abstract: In this paper, the performance of a helicopter engine’s combustion chamber burning sustainable aviation fuels is studied using both experimental and numerical approaches. Experiments were conducted at the Swedish Maritime Agency base in Kristanstad, Sweden, examining the emission profiles of the main exhaust species from one of the two Pratt & Whitney PT6C-67C engines mounted on a Leonardo AW139 helicopter. The fuels tested were Jet A and a HEFA-based SAF from Air BP. Mass spectrometer analysis of these fuels indicated that their chemical compositions can be represented by a blend of the HyChem reaction mechanisms for fossil Jet A (A2) and the Category C test fuel C1, HyChem A2/C1. This set of fuels was used to simulate the combustion process in a sector of the engine, highlighting the differences between the fuels. A Finite Rate Chemistry (FRC) Large Eddy Simulation (LES) model was employed, coupled with a Lagrangian field, representing the thermochemical properties and dynamics of the liquid fuel spray. The numerical predictions showed qualitative agreement with the experimental data. The distribution of species indicated that combustion proceeds as a Rich-Burn, Quick-Mix, Lean-Burn (RQL) three-stage process, with dilution of combustion products gradually offsetting the combustion products to reduce NOX. The combustor geometry resulted in skew symmetric velocity and temperature distributions. Only small differences were observed between the combustion of the different fuels.
