Regenerative-Cooling Heat-Transfer Performance of Mg/CO2 Powder Rocket Engines for Mars Missions

Supeng, Zhu; Wei, Ronggang; Hu, Chunbo; Li, Chao

doi:10.1007/s42405-022-00563-3

Cited by 1 publication

(3 citation statements)

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“…The software being open source provides the user the freedom to modify the particular correlations. Additionally, 1-D analyses usually over-predict the temperature as also encountered in [13]. However, the authors of that study also rightfully state that the aim of a 1-D thermal analysis is to provide a rapid estimation of the trends rather than very accurate estimations.…”

Section: Resultsmentioning

confidence: 99%

“…where N is the number of channels, L is the length of the particular section, and the superscript j denotes the section index. At each section, the heat flux is calculated by Equation ( 12) using the temperature of the coolant calculated at the previous section by Equation (13). Furthermore, the inner wall temperature is calculated as follows:…”

Section: Algorithm Of the Coolant Statementioning

confidence: 99%

“…They analyzed different channel configurations of engines with kerosene, and reported good agreement with experimental coolant pressure and temperature measurements. A recent study by Zhu et al [13] on a CO 2 /Mg engine, which is regeneratively cooled by CO 2 , included a 1-D model, in which the thermal effects of the channel geometry were examined. Heat transfer characteristics in different phase regimes of CO 2 were analyzed, and the results of the model were compared with the data of an experimental work.…”

Section: Introductionmentioning

confidence: 99%

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Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Kose,

Celik

2023

Applied Sciences

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Due to the extreme temperatures inside the combustion chambers of liquid propellant rocket engines, the walls of the combustion chamber and the nozzle are cooled by either the fuel or the oxidizer in what is known as regenerative cooling. This study presents an indigenous computational tool developed for the analysis of heat transfer in regenerative cooling of such rocket engines. The developed tool incorporates a one-dimensional (1-D) combustion analysis to calculate the thermophysical properties of the combustion gas. Basic engine properties were calculated and used to generate a thrust chamber profile based on a bell-shaped nozzle. The hot gas side was analyzed using 1-D isentropic flow assumptions, along with heat transfer correlations. The coolant side was evaluated using the hydraulic analysis in the axial direction and the heat transfer analysis in the radial direction. Thermophysical properties and the phase of the coolant were determined using the given property tables and the instantaneous state of the coolant. This flexible and computationally less demanding tool was used to analyze two small-scale engines utilizing liquid hydrocarbon fuels, which are used in modern rocket propulsion. The wall cooling analyses of a liquid oxygen (LOX)/liquid methane (LCH4) engine and a liquid oxygen (LOX)/liquid propane (LC3H8) engine are presented. Fuel and oxidizer were used separately as coolants for both engines, and both of them experienced phase change. Results reveal the advantage of the high mass flow rate of the oxidizer in cooling performance. In addition, the results of this study show that the cooling of the LOX/LC3H8 engine is somewhat more challenging compared to the LOX/LCH4 engine.

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Section: Resultsmentioning

confidence: 99%

Section: Algorithm Of the Coolant Statementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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