Abstract In this study, a novel expander rocket engine cycle that uses a third fluid as the combustor coolant and the turbine driver was discussed. A detailed system scheme with two stage cryogenic heat exchangers of the third fluid cooled (TFC) liquid rocket engine was improved. The design highlighted the phase-change heat transfer model of the regenerative cooling channels (RCC) on the basis of previous experiments. Subsequently, the state parameters distribution for the system was first proposed. In addition, the exergy analysis of cooled Rankine cycle (CRC) loop was investigated. The effects of the third fluid methane mass flow rate () on the exergy efficiency of CRC loop were further analyzed. The results demonstrated that the and the design geometric dimension of the RCC can well meet the thermal protection requirements of the thrust chamber. In the exergy analysis process, the exergy loss of the RCC was the largest. The exergy loss ratio of cryogenic heat exchanger Ⅰ and Ⅱ vary greatly due to the difference of the heat transfer performance. With the increase of the , the exergy efficiency of CRC loop decreased slightly, while the maximum output power from the heat transferred through the thrust chamber wall () increased. The results will be benefit for a better thermal performance of the TFC engine through the optimization of the and subassemblies.
Highlights The system scheme of third fluid cooled engine with two stage cryogenic heat exchangers is developed. The phase-change heat transfer model of subcritical cryogenic fluid is proposed on the basis of the experimental correlation. The distribution of state parameters and exergy analysisfor third fluid cooled engine are initially considered.
System scheme and thermal performance of a third fluid cooled rocket engine
Acta Astronautica ; 191 ; 204-215
2021-11-03
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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