The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found very effective. Then a laboratory scale ram combustor was fabricated and combustion tests were carried out mainly at the simulated condition of Mach 5. A vitiation technique was used to simulate a high temperature of 1263 K. The test results indicate that ignition, flame stability, and combustion efficiency were not significant, but the NOx emissions are a critical problem for the ram combustor at Mach 5 condition.
Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor
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Kinoshita, Y., Kitajima, J., Seki, Y., and Tatara, A. (July 1, 1995). "Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor." ASME. J. Eng. Gas Turbines Power. July 1995; 117(3): 394–400. https://doi.org/10.1115/1.2814108
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