Aerodynamic Investigation of Guide Vane Configurations Downstream a Rotating Detonation Combustor

Abstract Any outlet restriction downstream of pressure gain combustion (PGC), such as turbine blades, affects its flow field and may cause additional thermodynamic losses. The unsteadiness in the form pressure, temperature, velocity vector fluctuations has a negative impact on operation conventional turbines. Additionally, experimental measurements data acquisition present researchers with challenges that have to do mostly high temperature exhaust PGC frequency operation. Nevertheless, numerical simulations can provide important insights into interaction blades. In this paper, rotating detonation combustor (RDC) row nozzle guide vanes been modeled based from literature an available setup. Unsteady Reynolds-averaged Navier–Stokes (URANS) were done for five vane configurations different geometrical parameters investigate effect solidity blade type representing restrictions RDC flow. results analyzed connection between total loss thickness chord ratio. It is observed more than 57% upstream angle fluctuation amplitude was damped by vanes. Furthermore, area reduction found be significant driving factor damping fluctuations, whether or ratio increment. This investigation primary step turbomachinery standpoint, which provided details behavior unsteady field.