Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow
The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive f...
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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| Schlagwörter: |
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| Umfang: |
8 |
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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:129 ; year:2016 ; pages:44-51 ; extent:8 |
| Links: |
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| DOI / URN: |
10.1016/j.actaastro.2016.08.034 |
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ELV029441838 |
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| 520 | |a The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. | ||
| 520 | |a The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. | ||
| 650 | 7 | |a OpenFOAM |2 Elsevier | |
| 650 | 7 | |a Equivalence ratio |2 Elsevier | |
| 650 | 7 | |a Rearwall-expansion cavity |2 Elsevier | |
| 650 | 7 | |a Fuel injection scheme |2 Elsevier | |
| 650 | 7 | |a Optimization |2 Elsevier | |
| 700 | 1 | |a Wang, Zhenguo |4 oth | |
| 700 | 1 | |a Sun, Mingbo |4 oth | |
| 700 | 1 | |a Bai, Xue-Song |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.2016.08.034 doi GBVA2016002000003.pica (DE-627)ELV029441838 (ELSEVIER)S0094-5765(16)30640-3 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow 2016transfer abstract 8 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. OpenFOAM Elsevier Equivalence ratio Elsevier Rearwall-expansion cavity Elsevier Fuel injection scheme Elsevier Optimization Elsevier Wang, Zhenguo oth Sun, Mingbo oth Bai, Xue-Song 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:129 year:2016 pages:44-51 extent:8 https://doi.org/10.1016/j.actaastro.2016.08.034 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 129 2016 44-51 8 045F 520 |
| spelling |
10.1016/j.actaastro.2016.08.034 doi GBVA2016002000003.pica (DE-627)ELV029441838 (ELSEVIER)S0094-5765(16)30640-3 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow 2016transfer abstract 8 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. OpenFOAM Elsevier Equivalence ratio Elsevier Rearwall-expansion cavity Elsevier Fuel injection scheme Elsevier Optimization Elsevier Wang, Zhenguo oth Sun, Mingbo oth Bai, Xue-Song 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:129 year:2016 pages:44-51 extent:8 https://doi.org/10.1016/j.actaastro.2016.08.034 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 129 2016 44-51 8 045F 520 |
| allfields_unstemmed |
10.1016/j.actaastro.2016.08.034 doi GBVA2016002000003.pica (DE-627)ELV029441838 (ELSEVIER)S0094-5765(16)30640-3 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow 2016transfer abstract 8 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. OpenFOAM Elsevier Equivalence ratio Elsevier Rearwall-expansion cavity Elsevier Fuel injection scheme Elsevier Optimization Elsevier Wang, Zhenguo oth Sun, Mingbo oth Bai, Xue-Song 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:129 year:2016 pages:44-51 extent:8 https://doi.org/10.1016/j.actaastro.2016.08.034 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 129 2016 44-51 8 045F 520 |
| allfieldsGer |
10.1016/j.actaastro.2016.08.034 doi GBVA2016002000003.pica (DE-627)ELV029441838 (ELSEVIER)S0094-5765(16)30640-3 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow 2016transfer abstract 8 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. OpenFOAM Elsevier Equivalence ratio Elsevier Rearwall-expansion cavity Elsevier Fuel injection scheme Elsevier Optimization Elsevier Wang, Zhenguo oth Sun, Mingbo oth Bai, Xue-Song 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:129 year:2016 pages:44-51 extent:8 https://doi.org/10.1016/j.actaastro.2016.08.034 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 129 2016 44-51 8 045F 520 |
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10.1016/j.actaastro.2016.08.034 doi GBVA2016002000003.pica (DE-627)ELV029441838 (ELSEVIER)S0094-5765(16)30640-3 DE-627 ger DE-627 rakwb eng 520 520 DE-600 610 VZ 600 670 VZ 51.00 bkl Cai, Zun verfasserin aut Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow 2016transfer abstract 8 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. OpenFOAM Elsevier Equivalence ratio Elsevier Rearwall-expansion cavity Elsevier Fuel injection scheme Elsevier Optimization Elsevier Wang, Zhenguo oth Sun, Mingbo oth Bai, Xue-Song 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:129 year:2016 pages:44-51 extent:8 https://doi.org/10.1016/j.actaastro.2016.08.034 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 129 2016 44-51 8 045F 520 |
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Enthalten in Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? Amsterdam [u.a.] volume:129 year:2016 pages:44-51 extent:8 |
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effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow |
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Effect of combustor geometry and fuel injection scheme on the combustion process in a supersonic flow |
| abstract |
The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. |
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The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. |
| abstract_unstemmed |
The combustion process in a hydrogen fueled scramjet combustor with a rearwall-expansion cavity was investigated numerically under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. The numerical solver was first evaluated for supersonic reactive flows in a similar combustor configuration where experimental data is available. Wall-pressure distribution was compared with the experiments, and grid independency analysis and chemical mechanism comparison were conducted. The numerical results showed fairly good agreements with the available experimental data under supersonic combustion conditions. Then the numerical solver was used to study the effects of combustor geometry, fuel injection scheme and injection equivalence ratio on the combustion process. It was found that under the same fuel injection condition, the combustor configuration with a rearwall-expansion cavity is in favor of the supersonic combustion mode and present better ability of thermal choking prevention than the other combustor configurations. For the rearwall-expansion cavity combustor, the supersonic flow field was found to be sensitive to the injector position and injection scheme, but not highly sensitive to the injection pressure. Besides, rearwall-expansion cavity with the combined fuel injection scheme (with an injection upstream the cavity and a direct injection on the rear wall) is an optimized injection scheme during the flame stabilization process. |
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