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An air heater based on the combustor of liquid rocket engine is designed and studied.The combustion process of the test facility is researched through the numerical methods,and the hot-fire tests are performed to evaluate its performance.A total temperature rake is designed to measure the distribution of total temperature on the nozzle exit.Some conclusions are obtained by analyzing the flowpath dynamics of the air heater.Stable combustion is attained since the tripropellant gas-liquid coaxial injectors are adopted in the facility,and the air injecting from injectors fills in the region between the chamber wall and injectors,which protects the faceplate effectively.The lengths of flame are large because of the low evaporation rate of the droplet.But the gas mixes well in the chamber,and the high quality flow field of nozzle exit is obtained.The simulation solution is shown to agree with the total temperature rake data.