Walter F. O'Brien

TL;DR: A streamline curvature (SLC) throughflow numerical model was assessed and modified to better approximate the flow fields of highly transonic fans typical of military fighter applications to ensure accurate and reliable off-design performance prediction.

TL;DR: In this article, the authors explored the use of a continuous operation plasma torch as an ignitor and flameholder for scramjet combustion and found that it was a good flameholder in that both hydrogen and hydrocarbon fuels could be stabilized by the torch.

TL;DR: In this paper, an integrated fuel-injection/ignition system, consisting of an aeroramp injector and a plasma-torch igniter, was investigated in a supersonic wind tunnel.

TL;DR: In this article, the results from combustion experiments in a direct-connect supersonic combustor facility are presented, where successful ignition and sustained combustion of both hydrogen and ethylene fuels were achieved using an integrated aerorampinjector/plasma-torch igniter configuration.

TL;DR: The Turbine Engine Analysis Compressor Code (TEACC) as mentioned in this paper is a new simulation tool for inlet distortion analysis of a transonic NASA rotor, Rotor 1B. TEACC solves the compressible, time-dependent, threedimensional Euler equations modified to include turbomachinery source terms, which represent the effect of the blades.