Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow
In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impac...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Cai, Zun [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2016transfer abstract |
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| Umfang: |
7 |
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| Übergeordnetes Werk: |
Enthalten in: Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? - Al-Hamid, Hussein ELSEVIER, 2016, journal of the International Academy of Astronautics, Amsterdam [u.a.] |
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| Übergeordnetes Werk: |
volume:121 ; year:2016 ; pages:88-94 ; extent:7 |
| Links: |
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| DOI / URN: |
10.1016/j.actaastro.2015.12.030 |
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ELV029439345 |
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| 520 | |a In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. | ||
| 520 | |a In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. | ||
| 650 | 7 | |a Ignition scheme |2 Elsevier | |
| 650 | 7 | |a Partially covered cavity |2 Elsevier | |
| 650 | 7 | |a Injection setup |2 Elsevier | |
| 650 | 7 | |a Baffle |2 Elsevier | |
| 700 | 1 | |a Sun, Mingbo |4 oth | |
| 700 | 1 | |a Wang, Hongbo |4 oth | |
| 700 | 1 | |a Wang, Zhenguo |4 oth | |
| 773 | 0 | 8 | |i Enthalten in |n Elsevier Science |a Al-Hamid, Hussein ELSEVIER |t Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? |d 2016 |d journal of the International Academy of Astronautics |g Amsterdam [u.a.] |w (DE-627)ELV014615371 |
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10.1016/j.actaastro.2015.12.030 doi GBVA2016002000003.pica (DE-627)ELV029439345 (ELSEVIER)S0094-5765(15)30094-1 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. Ignition scheme Elsevier Partially covered cavity Elsevier Injection setup Elsevier Baffle Elsevier Sun, Mingbo oth Wang, Hongbo oth Wang, Zhenguo oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:121 year:2016 pages:88-94 extent:7 https://doi.org/10.1016/j.actaastro.2015.12.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 121 2016 88-94 7 045F 520 |
| spelling |
10.1016/j.actaastro.2015.12.030 doi GBVA2016002000003.pica (DE-627)ELV029439345 (ELSEVIER)S0094-5765(15)30094-1 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. Ignition scheme Elsevier Partially covered cavity Elsevier Injection setup Elsevier Baffle Elsevier Sun, Mingbo oth Wang, Hongbo oth Wang, Zhenguo oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:121 year:2016 pages:88-94 extent:7 https://doi.org/10.1016/j.actaastro.2015.12.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 121 2016 88-94 7 045F 520 |
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10.1016/j.actaastro.2015.12.030 doi GBVA2016002000003.pica (DE-627)ELV029439345 (ELSEVIER)S0094-5765(15)30094-1 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. Ignition scheme Elsevier Partially covered cavity Elsevier Injection setup Elsevier Baffle Elsevier Sun, Mingbo oth Wang, Hongbo oth Wang, Zhenguo oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:121 year:2016 pages:88-94 extent:7 https://doi.org/10.1016/j.actaastro.2015.12.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 121 2016 88-94 7 045F 520 |
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10.1016/j.actaastro.2015.12.030 doi GBVA2016002000003.pica (DE-627)ELV029439345 (ELSEVIER)S0094-5765(15)30094-1 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. Ignition scheme Elsevier Partially covered cavity Elsevier Injection setup Elsevier Baffle Elsevier Sun, Mingbo oth Wang, Hongbo oth Wang, Zhenguo oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:121 year:2016 pages:88-94 extent:7 https://doi.org/10.1016/j.actaastro.2015.12.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 121 2016 88-94 7 045F 520 |
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10.1016/j.actaastro.2015.12.030 doi GBVA2016002000003.pica (DE-627)ELV029439345 (ELSEVIER)S0094-5765(15)30094-1 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. Ignition scheme Elsevier Partially covered cavity Elsevier Injection setup Elsevier Baffle Elsevier Sun, Mingbo oth Wang, Hongbo oth Wang, Zhenguo oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:121 year:2016 pages:88-94 extent:7 https://doi.org/10.1016/j.actaastro.2015.12.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 121 2016 88-94 7 045F 520 |
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It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. 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Experimental investigation on ignition schemes of partially covered cavities in a supersonic flow |
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In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. |
| abstractGer |
In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. |
| abstract_unstemmed |
In this study, ignition schemes of the partially covered cavity in a scramjet combustor were investigated under inflow conditions of Ma=2.1 with stagnation pressure P 0 =0.7Mpa and stagnation temperature T 0 =947K. It reveals that the ignition scheme of the partially covered cavity has a great impact on the ignition and flame stabilization process. There always exists an optimized global equivalence ratio of a fixed ignition scheme, and the optimized global equivalence ratio of ignition in the partially covered cavity is lower than that of the uncovered cavity. For tandem dual-cavities, ignition in the partially covered cavity could be enhanced with the optimization of global equivalence ratio. However, ignition in the partially covered cavity would be exacerbated with further increasing the global equivalence ratio. The global equivalence ratio and the jet penetration height have a strong coupling with the combustion flow-field. For multi-cavities, it is assured that fuel injection on the opposite side could hardly be ignited after ignition in the partially covered cavity even with the optimized global equivalence ratio. It is possible to realize ignition enhancement in the partially covered cavity with the optimization of global equivalence ratio, but it is not beneficial for thrust increment during the steady combustion process. |
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