Pre-test computational fluid dynamics (CFD) data have been generated for an experimental scramjet combustor concept. These calculations represent the first step of a research initiative at Wright-Patterson Air Force Base that combines state-of-the-art experimental facilities with CFD towards the development of scramjet propulsion technologies. Both cold flow and reacting simulations have been performed for a baseline combustor pilot concept that consists of a wall mounted fuel injection system combined with a cavity flameholder. Results show reasonable mixing levels with minimal total pressure losses. Reacting simulations have shown that further refinements are needed to the combustor geometry to prevent thermal choking under certain conditions. Data obtained from CFD have proven beneficial to the experimental program by directing tests towards evaluating potential problems revealed by the calculations. Preliminary comparisons with measurements were favorable.

A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications

In flowfields created by transverse injection into supersonic cross-flows, the bow and separation shocks formed upstream of the injectant plume are dominant features. In the present investigation, the interaction between these features and the large-scale eddies that develop at the jet/freestream interface has been examined.

Bow shock/jet interaction in compressible transverse injection flowfields

An innovative pressure-measurement technique that employs the tools of molecular spectroscopy has been widely investigated by the aerospace community Measurements are made via oxygen-sensitive molecules attached to the surface of interest as a coating, or paint The pressure-sensitive-paint (PSP) technique is now commonly used in stationary wind-tunnel tests; this paper presents the use of this technique in advanced turbomachinery applications New pressure- and temperature-sensitive paints (P/TSPs) have been developed for application to a state-of-the-art transonic compressor where pressures up to 14 atm and surface temperatures to 90°C are expected for the suction surface of the first-stage rotor PSP and TSP data images have been acquired from the suction surface of the first-stage rotor at 85% of the corrected design speed for the compressor near-stall condition A comparison to over-the-rotor pressure transducer measurements will be presented© 2000 ASME

The Application of Pressure- and Temperature-Sensitive Paints to an Advanced Compressor

Supersonic combustion experiments were performed using three different hydrogen fuel-injection configurations in a cavity-based model scramjet combustor with various global fuel–air equivalence ratios. The configurations tested were angled injection at 15° to the flow direction upstream of the cavity, parallel injection from the front step, and upstream injection from the rear ramp. Planar laser-induced fluorescence of the hydroxyl radical and time-resolved pressure measurements were used to investigate the flow characteristics. Angled injection generated a weak bow shock in front of the injector and recirculation zone to maintain the combustion as the equivalence ratio increased. Parallel and upstream injections both showed similar flame structure over the cavity at low equivalence ratio. Upstream injection enhanced the fuel diffusion and enabled ignition with a shorter delay length than with parallel injection. The presence of a flame near the cavity was determined while varying the fuel injection location, the equivalence ratio, and total enthalpy of the air flow. The flame characteristics agreed with the correlation plot for the stable flame limit of non-premixed conditions. The pressure increase in the cavity for reacting flow compared to non-reacting flow was almost identical for all three configurations. More than 300 mm downstream of the duct entrance, averaged pressure ratios at low global equivalence ratio were similar for all three injection configurations.

https://www.mdpi.com/1996-1073/13/1/193/pdf

The Effect of Fuel Injection Location on Supersonic Hydrogen Combustion in a Cavity-Based Model Scramjet Combustor

Mixing Augmentation with Cooled Pylon Injection in a Scramjet Combustor

Surface pressure measurements in supersonic transverse injection flowfields

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Surface pressure measurements in supersonic transverse injection flowfields