An experiment is being developed to characterize the dynamics of liquid propellant rocket injectors. A single shear coaxial injector will feed gaseous oxygen and hydrogen into a pressurized chamber. Ignition is provided by a torch ignitor. To extend run times, film cooling by coflowing gaseous nitrogen is used to reduce the heat transfer to the chamber walls and nozzle. The injector base and four chamber segments are sealed with O-rings and held together by a hydraulic jack. Chamber gases exit through a water-cooled copper nozzle retained by an outlet flange secured with retaining bolts. The chamber is designed for rapid self-disassembly in case of an overpressure event that exceeds 15.7 MPa (2270 psi). Data collection will include acoustic signatures, chamber pressure and vibrations, wall and flow temperatures, flow imaging, and combustion diagnostics through an optical access window in the chamber. Experiments will be used to provide high-fidelity data to benchmark combustion stability analysis tools.
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