Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in  Rocket Engine Cooling Channels

Arun, M.; Akhil, J.; Noufal, K.; Baby, Robin; Babu, D. Vidyanadha; Prakash, M.

doi:10.5098/hmt.8.23

Cited by 3 publications

(1 citation statement)

References 24 publications

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“…Similar results were obtained by CFD simulations and can be found, for example, in [19]. This is remarkable because the mass flow per sector is identical and that means less coolant per channel for a higher aspect ratio, because the number of cooling channels increases with increasing aspect ratios, and therefore a higher _ q w ∕G.…”

Section: Influence Of the Aspect Ratiosupporting

confidence: 87%

Experimental Study of Methane Heat Transfer Deterioration in a Subscale Combustion Chamber

Haemisch

Suslov

Oschwald

2019

Journal of Propulsion and Power

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Methane has many possible advantages as a fuel for reusable rocket engines and is therefore extensively discussed. However, the characteristics of methane as a coolant in a regenerative cooling system are widely unknown. Especially the heat transfer deterioration that occurs in the vicinity of the critical point is a major concern and a severe drawback. To investigate this phenomenon and to establish a broad data basis for the validation of numerical simulations, tests were performed with a subscale combustion chamber. The combustion chamber contains different cooling channel geometries (rectangular cooling channels with the aspect ratios [height-to-width ratio]: 1.7, 3.5, 9.2, and 30) and was cooled with cryogenic methane. Results close to the critical point show a distinct maximum in hot gas wall temperature, which is a clear evidence of heat transfer deterioration. The test results indicate a strong dependency on the occurrence of this effect toward cooling channels with a low aspect ratio.

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Section: Influence Of the Aspect Ratiosupporting

confidence: 87%

Experimental Study of Methane Heat Transfer Deterioration in a Subscale Combustion Chamber

Haemisch

Suslov

Oschwald

2019

Journal of Propulsion and Power

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Numerical Analysis of a Supercritical Heat Transfer of Cryogenic Methane in Regeneratively Cooled Rocket Engine

DJEFFAL,

BENAMARA,

LAHCENE

et al. 2024

INCAS BULLETIN

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A comparative study of supercritical heat transfer in a regeneratively cooled rocket engine was conducted using three-dimensional numerical simulations for two channel geometries: rectangular and square. Various constant heat fluxes, flow velocities, and operating pressures were imposed to study their effect on heat transfer, pressure losses, and the conditions under which heat transfer deterioration HTD occurs. The results show that a rectangular channel is more efficient in terms of heat transfer than a square channel, with a more pronounced difference at high heat fluxes and low velocities, these conditions, in fact, favored the occurrence of heat transfer deterioration, particularly in the square channel. Increasing the flow velocities to reduce the wall temperature and prevent thermal deterioration was accompanied by a significant increase in pressure losses, these pressure losses are greater in the rectangular channel, despite its advantages in terms of heat transfer. Operating pressure also plays an important role in heat transfer, increasing the pressure results in a decrease in wall temperature.

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Study on Two-Phase Pressure Drop of Methane during Flow Boiling in Mini Channel

Song,

Li,

Sun

et al. 2023

DDF

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For LOX/LCH4 variable thrust rocket engine, the propellant methane is traditionally selected as the coolant in regenerative cooling channel (RCC). With the decrease of engine thrust, the mass flow rate of coolant methane decreases gradually. At low engine thrust, the coolant methane is usually in a subcritical state. The heat transfer deterioration of subcritical methane occurs in RCC, which may cause thrust chamber wall ablation. The two-phase pressure drop data of methane are crucial parameters for the design and optimization of RCC. But it is rarely to find such measured frictional pressure drop data of methane in open published literature. The two-phase pressure drop of methane during flow boiling in the single mini channels with the diameters of 2.0 mm are investigated systematically. Effects of the mass flux (582.19~1755.48 kg/m2·s), inlet pressure (0.56~3.55 MPa), heat flux (53.25~318.68 kW/m2) on the frictional pressure drop of methane are discussed. The results show that the frictional pressure drop of methane during flow boiling increases with mass flux and inlet pressure at the experimental conditions, and heat flux shows weak effect on the frictional pressure drop. The comparisons of the experimental data with the predicted value by existing six correlations are analyzed. Contrary to the conventional channels, homogeneous model yields better prediction than five separated flow models. Present experimental results can provide reference for the design and optimization of RCC in LOX/LCH4 rocket engine.

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Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in Rocket Engine Cooling Channels

Cited by 3 publications

References 24 publications

Experimental Study of Methane Heat Transfer Deterioration in a Subscale Combustion Chamber

Experimental Study of Methane Heat Transfer Deterioration in a Subscale Combustion Chamber

Numerical Analysis of a Supercritical Heat Transfer of Cryogenic Methane in Regeneratively Cooled Rocket Engine

Study on Two-Phase Pressure Drop of Methane during Flow Boiling in Mini Channel

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