Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions
Hydrocarbon impurities in Liquified Natural Gas LNG may produce undesired phenomena such as pseudo boiling and two-phase flow. This can be an issue for rocket engine cooling channels. This study investigates the impacts of hydrocarbon impurities on LNG thermophysical and transport properties. It est...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
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Elsevier
2023-11-01
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| Series: | International Journal of Thermofluids |
| Subjects: | |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2666202723001763 |
| _version_ | 1827593583475032064 |
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| author | Ibraheem Nasser Oskar Haidn Chiara Manfletti |
| author_facet | Ibraheem Nasser Oskar Haidn Chiara Manfletti |
| author_sort | Ibraheem Nasser |
| collection | DOAJ |
| description | Hydrocarbon impurities in Liquified Natural Gas LNG may produce undesired phenomena such as pseudo boiling and two-phase flow. This can be an issue for rocket engine cooling channels. This study investigates the impacts of hydrocarbon impurities on LNG thermophysical and transport properties. It estimates the required relative roughness to improve the cooling capabilities with appropriate pressure drops for different LNG mixtures flowing in the rocket engine cooling channel. The Reynolds-averaged-Navier–Stokes equations are numerically solved for a straight cooling channel with a circular cross-section and uniform heat flux. LNG’s thermophysical and transport properties are calculated using the GERG equation of state and extended corresponding states, respectively. The turbulent models are validated numerically for supercritical LNG, vapor methane, and supercritical hydrogen. The results show that hydrocarbon compositions play a significant role in cricondenbar pressure. When the hydrocarbon impurities increase, the phase envelope develops, and cricondenbar pressure increases. The impacts of various relative wall roughness configurations on the cooling capabilities and pressure drops are sensitive under transcritical processes and hydrocarbon compositions. This study provides a systematic understanding of the relationships between cooling channel surface roughness, Nusselt Number, and LNG composition, offering designers the ability to optimize heat transfer in rocket engine cooling systems. |
| first_indexed | 2024-03-09T02:13:44Z |
| format | Article |
| id | doaj.art-77e0d70d5d774e5d99abbb0057399e47 |
| institution | Directory Open Access Journal |
| issn | 2666-2027 |
| language | English |
| last_indexed | 2024-03-09T02:13:44Z |
| publishDate | 2023-11-01 |
| publisher | Elsevier |
| record_format | Article |
| series | International Journal of Thermofluids |
| spelling | doaj.art-77e0d70d5d774e5d99abbb0057399e472023-12-07T05:30:50ZengElsevierInternational Journal of Thermofluids2666-20272023-11-0120100461Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditionsIbraheem Nasser0Oskar Haidn1Chiara Manfletti2Corresponding author.; Chair of Space Propulsion and Mobility, Technical University of Munich, Ottobrunn, 85521, GermanyChair of Space Propulsion and Mobility, Technical University of Munich, Ottobrunn, 85521, GermanyChair of Space Propulsion and Mobility, Technical University of Munich, Ottobrunn, 85521, GermanyHydrocarbon impurities in Liquified Natural Gas LNG may produce undesired phenomena such as pseudo boiling and two-phase flow. This can be an issue for rocket engine cooling channels. This study investigates the impacts of hydrocarbon impurities on LNG thermophysical and transport properties. It estimates the required relative roughness to improve the cooling capabilities with appropriate pressure drops for different LNG mixtures flowing in the rocket engine cooling channel. The Reynolds-averaged-Navier–Stokes equations are numerically solved for a straight cooling channel with a circular cross-section and uniform heat flux. LNG’s thermophysical and transport properties are calculated using the GERG equation of state and extended corresponding states, respectively. The turbulent models are validated numerically for supercritical LNG, vapor methane, and supercritical hydrogen. The results show that hydrocarbon compositions play a significant role in cricondenbar pressure. When the hydrocarbon impurities increase, the phase envelope develops, and cricondenbar pressure increases. The impacts of various relative wall roughness configurations on the cooling capabilities and pressure drops are sensitive under transcritical processes and hydrocarbon compositions. This study provides a systematic understanding of the relationships between cooling channel surface roughness, Nusselt Number, and LNG composition, offering designers the ability to optimize heat transfer in rocket engine cooling systems.http://www.sciencedirect.com/science/article/pii/S2666202723001763Cooling channelSupercritical pressureLiquefied natural gasLiquid rocket engineHeat transfer |
| spellingShingle | Ibraheem Nasser Oskar Haidn Chiara Manfletti Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions International Journal of Thermofluids Cooling channel Supercritical pressure Liquefied natural gas Liquid rocket engine Heat transfer |
| title | Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions |
| title_full | Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions |
| title_fullStr | Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions |
| title_full_unstemmed | Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions |
| title_short | Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions |
| title_sort | numerical investigation of rocket engine cooling channel heat transfer for different lng under trans critical conditions |
| topic | Cooling channel Supercritical pressure Liquefied natural gas Liquid rocket engine Heat transfer |
| url | http://www.sciencedirect.com/science/article/pii/S2666202723001763 |
| work_keys_str_mv | AT ibraheemnasser numericalinvestigationofrocketenginecoolingchannelheattransferfordifferentlngundertranscriticalconditions AT oskarhaidn numericalinvestigationofrocketenginecoolingchannelheattransferfordifferentlngundertranscriticalconditions AT chiaramanfletti numericalinvestigationofrocketenginecoolingchannelheattransferfordifferentlngundertranscriticalconditions |