Lean-Burn Combustor Simulator for an Engine-Component Test Facility: An Experimental and Computational Study

Abstract The computational and experimental assessment of a lean-burn low-NOx combustor simulator for an engine component test facility is presented. Engine Component Aero-Thermal (ECAT) full-scale engine-parts facility, designed the study aero-thermal performance fully cooled high-pressure nozzle guide vanes (NGVs). operates with non-dimensionally matched conditions in terms Reynolds number, Mach coolant-to-mainstream pressure ratio. to replicate swirl temperature distortion upstream vanes. purpose allow flow capacity, aerodynamic (with film cooling), thermal (overall effectiveness) presence engine-realistic inlet distortions. ECAT design builds on work Hall Povey, who developed low-speed atmospheric-pressure preliminary similar simulators later implemented Oxford Turbine Research Facility ECAT. This pilot produced non-dimensional combustor-exit closely target profiles representative modern aero engines. was modified scaled compatibility annulus-line higher-pressure operating facility. In present study, detailed measurements multi-hole probes thermocouples (pressure profile field) are presented compared results from Reynolds-Averaged Navier–Stokes Simulations. Additional simulations were performed understand how elevated back-pressure vane potential field affect loss, residual swirl, at combustor–turbine interface. perhaps most comprehensive date engine-scale research providing unique insight into known challenges design, scaling issues when moving low high limitations fluid dynamics this environment. results, which will serve as boundary impact components future studies demonstrate fidelity can be replicated non-reacting