پیوندهای مفید
آمار
| تعداد نشریات | 22 |
| تعداد شمارهها | 712 |
| تعداد مقالات | 10,258 |
| تعداد مشاهده مقاله | 72,013,260 |
| تعداد دریافت فایل اصل مقاله | 63,762,299 |
Numerical Investigation on Transient Heat Transfer of Different Coolants in the Cooling Channel of a Thrust Chamber | ||
| Journal of Heat and Mass Transfer Research | ||
| دوره 13، شماره 2 - شماره پیاپی 26، شهریور 2026، صفحه 206-218 اصل مقاله (1.98 M) | ||
| نوع مقاله: Full Length Research Article | ||
| شناسه دیجیتال (DOI): 10.22075/jhmtr.2026.40123.1914 | ||
| نویسندگان | ||
| Arash Haeri1؛ Hamidreza Farshi Fasih* 1؛ Roohollah Rafee2 | ||
| 1Department of Aerospace Engineering, Faculty of New Science and Technologies, Semnan University, Semnan, Iran | ||
| 2Faculty of Mechanical Engineering, Semnan University, Semnan, Iran | ||
| تاریخ دریافت: 09 بهمن 1404، تاریخ بازنگری: 14 اسفند 1404، تاریخ پذیرش: 23 اسفند 1404 | ||
| چکیده | ||
| Controlling the nozzle wall temperature using regenerative cooling is a highly effective approach in liquid rocket engines. The selection of coolant is critical to determining the cooling system's thermal performance. In this study, the transient and steady-state heat transfer characteristics of a regenerative cooling channel are numerically investigated using two benchmark coolants, water and Ethyl-alcohol, under different coolant mass flow rates. A two-dimensional axisymmetric conjugate heat transfer model is employed, in which the thrust chamber, cooling channel, and solid walls are fully coupled. For both coolants, the maximum gas-side wall temperature occurs upstream of the nozzle throat, and increasing the coolant mass flow rate significantly reduces both gas-side and coolant-side wall temperatures throughout the thrust chamber. Specifically, for water, the maximum wall temperature decreases from 657 K to 541 K as the mass flow rate increases from 0.5 to 1.5 kg/s, whereas for Ethyl-alcohol, it decreases from 957 K to 693 K. The time required to reach steady-state conditions for Ethyl-alcohol is approximately 1.8 times longer than that of water, while reducing the coolant mass flow rate from 1.0 to 0.5 kg/s nearly doubles the steady-state time. Moreover, the coolant mass flow rate strongly influences the peak heat flux and convective heat transfer coefficient upstream of the throat. Increasing the mass flow rate enhances heat transfer, so that at 1.5 kg/s the maximum heat flux is 21.0 MW/m² for water and 19.7 MW/m² for Ethyl-alcohol. Correspondingly, the convective heat transfer coefficient attains a peak value of approximately 7.8 kW/m²·K near the throat and increases with increasing coolant mass flow rate. The results provide quantitative insights into transient thermal behavior and heat transfer mechanisms in regenerative cooling channels, offering helpful guidance for the thermal design and optimization of rocket engine thrust chambers. | ||
| کلیدواژهها | ||
| Cooling channel؛ Wall temperature؛ Coolant؛ Heat flux؛ Convective heat transfer | ||
| عنوان مقاله [English] | ||
| بررسی عددی انتقال حرارت گذرای خنک کنندههای مختلف در کانال خنک کاری محفظه تراست | ||
| مراجع | ||
|
[1] Jeon, T. J., Park, T. S., 2024. Thermal recycling analysis in regenerative cooling channels based on liquid rocket engine cycles. Applied Thermal Engineering, 256, 124095. https://doi.org/10.1016/j.applthermaleng.2024.124095 [2] Leonardi, M., Pizzarelli, M., Nasuti, F., 2018. A numerical procedure for the design of cooling channels for liquid rocket engines. Space Propulsion Conference, SP2018-00158. [3] Pizzarelli, M., Carapellese, S., Nasuti, F., 2011. A quasi-2-D model for the prediction of the wall temperature of rocket engine cooling channels. Numerical Heat Transfer A, 60(1), pp. 1-24. http://dx.doi.org/10.1080/10407782.2011.578011 [4] Yang, W., Sun, B., 2013. Numerical simulation of liquid film and regenerative cooling in a liquid rocket. Applied Thermal Engineering, 54, pp. 460-469. http://dx.doi.org/10.1016/j.applthermaleng.2013.02.021 [5] Heldens, J. C., Fridh, J., Östlund, J., 2021. On the characterization of methane in rocket nozzle cooling channels. Acta Astronautica, 186, pp. 337–346. https://doi.org/10.1016/j.actaastro.2021.05.034 [6] Kim, S. K., Joh, M., Choi, S. H., Park, T. S., 2014. Effective modeling of conjugate heat transfer and hydraulics for the regenerative cooling design of kerosene rocket engines. Numerical Heat Transfer A, 66(8), pp. 863-883. http://dx.doi.org/10.1080/10407782.2014.892396 [7] Shanmugam, A. R., Park, K. S., 2024. Flow and heat transfer of supercritical hydrogen in a regenerative cooling channel with the arc ribs of a rocket engine. Applied Thermal Engineering, 236, 121451. https://doi.org/10.1016/j.applthermaleng.2023.121451 [8] Nasser, I., Haidn, O., Manfletti, C., 2023. Numerical investigation of rocket engine cooling channel heat transfer for different LNG under trans-critical conditions. International Journal of Thermofluids, 20, 100461. https://doi.org/10.1016/j.ijft.2023.100461 [9] Engblom, W., Fletcher, B., Georgiadis, N., 2008. Conjugate Conduction-Convection Heat Transfer for Water-Cooled High-Speed Flows. AIAA, 2008-4653. https://doi.org/10.2514/6.2008-4653 [10] Zhao, J., Li, S., Zhang, X., Sun, M., Song, Y., 2023. Enhanced heat transfer of supercritical n-decane in cooling channels with triangular ribs for regenerative cooling. Applied Thermal Engineering, 218, 119369. https://doi.org/10.1016/j.applthermaleng.2022.119369 [11] Wang, L., Chen, Z., Meng, H., 2013. Numerical study of conjugate heat transfer of cryogenic methane in rectangular engine cooling channels at supercritical pressures. Applied Thermal Engineering, 54, pp. 237-246. http://dx.doi.org/10.1016/j.applthermaleng.2013.02.007 [12] Zhang, X., Guo, W., Gao, G., Xi, W., Liu, J., Sunden, B., 2025. Numerical investigations of flow and heat transfer characteristics of a regenerative cooling channel using supercritical CO2 with different cross-section shapes. International Journal of Thermal Sciences, 215, 109965. https://doi.org/10.1016/j.ijthermalsci.2025.109965 [13] Buchholz, M., Gruber, S., Selbmann, A., Marquardt, A., Meier, L., Müller, M., Seifert, L., Leyens, C., Tajmar, M., Bach, C., 2023. Flow rate improvements in additively manufactured flow channels suitable for rocket engine application. CEAS Space Journal, 15, pp. 715-728. https://doi.org/10.1007/s12567-022-00476-7 [14] Zhou, C., Yu, N., Wang, S., Han, S., Gong, H., Cai, G., Wang, J., 2023. The influence of thrust chamber structure parameters on regenerative cooling effect with hydrogen peroxide as coolant in liquid rocket engines. Aerospace, 10, 65. https://doi.org/10.3390/aerospace10010065 [15] Junjie, L., Guanquan, D., Ping, J., Ruizhi, L., 2023. Heat transfer analysis and structural optimization for spiral channel regenerative cooling thrust chamber. International Journal of Aerospace Engineering, 8628107. https://doi.org/10.1155/2023/8628107 [16] Zhang, Q., Xue, T., Zhang, X., 2024. Advancing heat transfer efficiency: V-shape crossed structures in regenerative cooling channels for rocket engines. International Communications in Heat and Mass Transfer, 158, 107921. https://doi.org/10.1016/j.icheatmasstransfer.2024.107921 [17] Marchi, C. H., Laroca, F., Silva, A. F. C., Hinckel, J. N., 2004. Numerical solutions of flow in rocket engines with regenerative cooling. Numerical Heat Transfer A, 45, pp. 699-717. https://doi.org/10.1080/10407780490424307 [18] Song, J., Sun, B., 2016. Coupled numerical simulation of combustion and regenerative cooling in LOX/Methane rocket engines. Applied Thermal Engineering, 106, pp. 762-773. http://dx.doi.org/10.1016/j.applthermaleng.2016.05.130 [19] Shokri, M., Ebrahimi, A., 2018. Heat transfer aspects of regenerative-cooling in methane-based propulsion systems. Aerospace Science and Technology, 82, pp. 412-424. https://doi.org/10.1016/j.ast.2018.09.025 [20] Farshi Fasih, H., Ghassemi, H., Karimi Mazraeshahi, H., 2022. Numerical investigation on gasification process of heavy fuel oil in an entrained flow gasifier. Petroleum Science and Technology, 41, pp. 524-545. https://doi.org/10.1080/10916466.2022.2062383 [21] Song, J., Liang, T., Li, Q., Cheng, P., Zhang, D., Cui, P., Sun, J., 2021. Study on the heat transfer characteristics of regenerative cooling for LOX/LCH4 variable thrust rocket engine. Case Studies in Thermal Engineering, 28, 101664. https://doi.org/10.1016/j.csite.2021.101664 [22] Song, J., Cui, P., Li, Q., Cheng, P., Chen, L., Liang, T., 2022. System scheme and thermal performance of a third fluid cooled rocket engine. Acta Astronautica, 191, pp. 204-215. https://doi.org/10.1016/j.actaastro.2021.11.004 [23] Liu, S., Cheng, Q., Han, L., Zhang, W., Wang, G., Li, Y., 2024. The influence of asymmetric truncated ribs on flow and heat transfer of supercritical aviation kerosene in a rectangular curved cooling channel. International Journal of Thermal Sciences, 196, 108720. https://doi.org/10.1016/j.ijthermalsci.2023.108720 [24] Kostić, O. P., Stefanović, Z. A., Kostić, I. A., 2015. CFD modeling of supersonic airflow generated by 2D nozzle with and without an obstacle at the exit section. FME Transactions, 43, pp. 107-113. DOI:10.5937/FMET1502107K [25] Yan, Z., Chen, Y., Wu, Y., Liu, Z., Gao, Y., Wang, W., 2023. A system-level multi-field coupling algorithm for regenerative cooling thrust chamber of a LOX/methane rocket engine. Acta Astronautica, 213, pp. 588-602. https://doi.org/10.1016/j.actaastro.2023.09.042 [26] Kim, S. K., Joh, M., Choi, H. S., Park, T. S., 2014. Multidisciplinary simulation of a regeneratively cooled thrust chamber of liquid rocket engine: turbulent combustion and nozzle flow. International Journal of Heat and Mass Transfer, 70, pp. 1066-1077. http://dx.doi.org/10.1016/j.ijheatmasstransfer.2013.10.046 [27] Kang, Y. D., Sun, B., 2011. Numerical Simulation of Liquid Rocket Engine Thrust Chamber Regenerative Cooling. Journal of Thermophysics and Heat Transfer, 25, pp. 155-164. https://doi.org/10.2514/1.47701 [28] Ulas, A., Boysan, E., 2013. Numerical analysis of regenerative cooling in liquid propellant rocket engines. Aerospace Science and Technology, 24, pp. 187-197. https://doi.org/10.1016/j.ast.2011.11.006 [29] Gallo, G., Kamps, L., Hirai, S., Carmicino, C., Nagata, H., 2023. One-dimensional modelling of the nozzle cooling with cryogenic oxygen flowing through helical channels in a hybrid rocket. Acta Astronautica, 210, pp. 176-196. https://doi.org/10.1016/j.actaastro.2023.05.013 [30] Rajagopal, M., 2015. Numerical modeling of regenerative cooling system for large expansion ratio rocket engines. Journal of Thermal Science and Engineering Applications, 7, 011012. https://doi.org/10.1115/1.4028979 [31] Negishi, H., Daimon, Y., Negoro, N., Kurosu, A., 2015. Regenerative cooling performance analysis of the LE-X engine combustion chamber. AIAA, 2015-3760. https://doi.org/10.2514/6.2015-3760 [32] Eiringhaus, D., Riedmann, H., Knab, O., Haidn, O. J., 2019. 3D Conjugate heat transfer analysis of a 100 kN class liquid rocket combustion chamber. 8TH European conference for aeronautics and aerospace sciences. DOI: 10.13009/EUCASS2019-251 [33] Daimon, Y., Negishi, H., Kawashima, H., 2019. Conjugated combustion and heat transfer simulations of upper and lower main combustion chambers of LE-9 engine. AIAA, 2019-4112. https://doi.org/10.2514/6.2019-4112 [34] Naraghi, M.H., Dunn, S., Coats, D., 2004. A model for design and analysis of regeneratively cooled rocket engines. AIAA, 2004-3852. https://doi.org/10.2514/6.2004-3852 [35] Pu, H., Li, S., Dong, M., Jiao, S., Shang, Y., 2018. Numerical method for coupled thermal analysis of the regenerative cooling structure. Journal of Thermophysics and Heat Transfer, 23. https://doi.org/10.2514/1.T5224 [36] Fouladi, N., Farahani, M., Dowlatabadi, M. M., 2025. Cooling system design and analysis for high heat flux large dimension diffuser of a high-altitude test facility. International Journal of Thermofluids, 25, 101030. https://doi.org/10.1016/j.ijft.2024.101030 | ||
|
آمار تعداد مشاهده مقاله: 176 تعداد دریافت فایل اصل مقاله: 176 |
||