Experimental Analysis of Heat Transfer Deterioration and Pseudoboiling Phenomena in a Methane Cooled Combustion Chamber at Real Conditions

Haemisch, Jan; Suslov, Dmitry; Oschwald, Michael

doi:10.2514/6.2018-4943

Cited by 7 publications

(2 citation statements)

References 8 publications

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“…Methane and propane are two hydrocarbon fuels that are studied and used as rocket fuels and are also considered green propellants [14]. Especially with the advent of commercial rockets utilizing methane, LOX/liquid methane (LCH 4 ) engines have been studied extensively over the last two decades [15][16][17][18][19][20]. In some of these studies, 1-D regenerative cooling analyses of such engines were conducted.…”

Section: Introductionmentioning

confidence: 99%

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: Introductionmentioning

confidence: 99%

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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“…Extensive research has been conducted on the heat transfer process [9][10][11][12], correlation fitting [13][14][15], and channel configuration optimization [16][17][18] for regenerative cooling of methane in both supercritical and subcritical conditions. While there is a wealth of knowledge on supercritical heat transfer, the experimental research on subcritical cooling, which involves complex factors such as phase-change heat absorption and temperature gap heat transfer, is relatively limited.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Boiling Heat Transfer Characteristics of Liquid Methane in Mini Channel

Song,

Li,

Sun

et al. 2023

DDF

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LOX/LCH4 rocket engine has been recognized as the ideal power choice for future space vehicles due to the merits of low cost, non-toxic and pollution-free, convenient maintenance, suitable for reuse and high specific impulse. In the process of wide range variable thrust of LOX/LCH4 rocket engine, the coolant methane is in a subcritical state due to the low combustor pressure under low operation conditions. The instability of two-phase flow is easy to occur in regenerative cooling channel (RCC), and it is urgent to investigate the heat transfer performance of methane with phase change in RCC. Experiments have been conducted to investigate the flow boiling characteristics of liquid methane in the single mini channels with the diameters of 1.0, 1.5 and 2.0 mm. Effects of the mass flux (266.75~1781.26 kg/m2·s), inlet pressure (0.56~4.24 MPa), heat flux (53.25~800.07 kW/m2) and channel diameter (1.0~2.0 mm) on the flow boiling heat transfer coefficients are tested. Results show that there are two regions with different heat transfer mechanism, one is the nucleate boiling dominated region for low mass quality and the other is the convection evaporation dominated region for high mass quality. A new correlation expressed by Bo, We, Kp, X, Co, Ftg is proposed, which yields good fitting for 355 experimental data with a mean absolute error (MAE) of 10.9%. Present experimental results can provide reference for the thermal protection prediction and optimal design of RCC in LOX/LCH4 rocket engine.

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Experimental Investigations of Heat Transfer Processes in Cooling Channels for Cryogenic Hydrogen and Methane at Supercritical Pressure

Haemisch¹,

Suslov²,

Oschwald³

2020

Lecture Notes in Mechanical Engineering

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Experimental Analysis of Heat Transfer Deterioration and Pseudoboiling Phenomena in a Methane Cooled Combustion Chamber at Real Conditions

Cited by 7 publications

References 8 publications

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

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

Experimental Investigation on Boiling Heat Transfer Characteristics of Liquid Methane in Mini Channel

Experimental Investigations of Heat Transfer Processes in Cooling Channels for Cryogenic Hydrogen and Methane at Supercritical Pressure

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