Abstract
Simulations of a coupled supersonic inlet and fan were carried out for to analyze the effects of developed radial distortion on fan performance and stability. The coupling at the interface between the inlet and fan was accomplished using a mixing plane. An in-house implicit second-order solver with upwind discretization of fluxes and dual-time stepping for unsteady calculations was used. The Navier-Stokes equations were complemented by a ω κ - turbulence model. A choked nozzle with an adjustable throttle area was used for the outlet boundary to allow natural flow development and to control mass flow rate along a speed line. The inlet profiles at the aerodynamic interface plane were realistic in that they depended on the mass flow rate and the cowl lip shock location/shape. Total pressure losses varied from 4% in the free steam and up to 20% near the hub. The effect of distortion was reduced at lower mass flow rates recovering the performance. Unsteady simulations at unstable flow conditions beyond the stability limit were carried out as well. It was found that under these conditions a double loop was developed on the performance map as a result of coupling between the fan and cowl shock at the inlet.
Published Version
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