Parametric Modeling Investigation for Radially Staged Low-Emission Combustion

摘要

Aviation gas-turbine combustion demands high efficiency, wide operability, and minimal trace gas emissions. Performance critical design parameters include injector geometry, combustor layout, fuel-air mixing, and engine cycle conditions. The present investigation explores these factors and their impact on a radially staged low-emission aviation combustor sized for a next-generation 24,000-lbf-thrust engine. By coupling multifidelity computational tools, a design exploration was performed using a parameterized annular combustor sector at projected 100 % takeoff power conditions. Design objectives included nitrogen oxide emission indices and overall combustor pressure loss. From the design space, an optimal configuration was selected and simulated at 7.1, 30, and 85% part-power operation, corresponding to landing-takeoff cycle idle, approach, and climb segments. All results were obtained by solution of the steady-state Reynolds-averaged Navier-Stokes equations. Species concentrations were solved directly using a reduced 19-step reaction mechanism for Jet A. Turbulence closure was obtained using a nonlinear κ-ε model. This research demonstrates revolutionary combustor design exploration enabled by muitifidelity physics-based simulation.