Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine
Equivalent ratio (ER) is an important factor affecting detonation characteristics and propulsion performance of rotating detonation rocket engine (RDRE). In this paper, the effects of different equivalent ratios detonation characteristics and thrust performance of methane-oxygen RDRE were studied by...
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MDPI AG
2025-01-01
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| author | Xiao Xu Qixiang Han Yining Zhang |
| author_facet | Xiao Xu Qixiang Han Yining Zhang |
| author_sort | Xiao Xu |
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| description | Equivalent ratio (ER) is an important factor affecting detonation characteristics and propulsion performance of rotating detonation rocket engine (RDRE). In this paper, the effects of different equivalent ratios detonation characteristics and thrust performance of methane-oxygen RDRE were studied by 2D numerical simulation. The premixed reactants were injected through the injection holes to simulate the discrete injection of reactants on the injection panel in actual RDRE, the number of injection holes was 60 and 120. The results show that there is hybrid detonation mode (HDM), co-direction multi-wave detonation mode (CMM) and unstable detonation mode (UDM) in detonation combustion due to the influence of equivalent ratio and the number of injection holes, and the co-directional multi-wave detonation mode is beneficial to the thrust stability of RDRE. At the last, the number of detonation waves in RDRE decreases with the increase in the equivalent ratio, and the specific impulse (<i>I</i><sub>sp</sub>) increases with the increase of the equivalent ratio. |
| format | Article |
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| institution | Kabale University |
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| language | English |
| publishDate | 2025-01-01 |
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| spelling | doaj-art-96c7fbff74774964a43386195d3957be2025-01-24T13:15:43ZengMDPI AGAerospace2226-43102025-01-011216810.3390/aerospace12010068Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket EngineXiao Xu0Qixiang Han1Yining Zhang2College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaCollege of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaBeijing Power Machinery Institute, Beijing 100074, ChinaEquivalent ratio (ER) is an important factor affecting detonation characteristics and propulsion performance of rotating detonation rocket engine (RDRE). In this paper, the effects of different equivalent ratios detonation characteristics and thrust performance of methane-oxygen RDRE were studied by 2D numerical simulation. The premixed reactants were injected through the injection holes to simulate the discrete injection of reactants on the injection panel in actual RDRE, the number of injection holes was 60 and 120. The results show that there is hybrid detonation mode (HDM), co-direction multi-wave detonation mode (CMM) and unstable detonation mode (UDM) in detonation combustion due to the influence of equivalent ratio and the number of injection holes, and the co-directional multi-wave detonation mode is beneficial to the thrust stability of RDRE. At the last, the number of detonation waves in RDRE decreases with the increase in the equivalent ratio, and the specific impulse (<i>I</i><sub>sp</sub>) increases with the increase of the equivalent ratio.https://www.mdpi.com/2226-4310/12/1/68equivalent ratiodetonation characteristicspropulsion performance |
| spellingShingle | Xiao Xu Qixiang Han Yining Zhang Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine Aerospace equivalent ratio detonation characteristics propulsion performance |
| title | Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine |
| title_full | Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine |
| title_fullStr | Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine |
| title_full_unstemmed | Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine |
| title_short | Numerical Investigation of the Effect of Equivalent Ratio on Detonation Characteristics and Performance of CH<sub>4</sub>/O<sub>2</sub> Rotating Detonation Rocket Engine |
| title_sort | numerical investigation of the effect of equivalent ratio on detonation characteristics and performance of ch sub 4 sub o sub 2 sub rotating detonation rocket engine |
| topic | equivalent ratio detonation characteristics propulsion performance |
| url | https://www.mdpi.com/2226-4310/12/1/68 |
| work_keys_str_mv | AT xiaoxu numericalinvestigationoftheeffectofequivalentratioondetonationcharacteristicsandperformanceofchsub4subosub2subrotatingdetonationrocketengine AT qixianghan numericalinvestigationoftheeffectofequivalentratioondetonationcharacteristicsandperformanceofchsub4subosub2subrotatingdetonationrocketengine AT yiningzhang numericalinvestigationoftheeffectofequivalentratioondetonationcharacteristicsandperformanceofchsub4subosub2subrotatingdetonationrocketengine |