Experimental investigation on ignition schemes of a supersonic combustor with the rearwall-expansion cavity
In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Cai, Zun [verfasserIn] |
|---|
| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2016transfer abstract |
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| Schlagwörter: |
Cavity direct spanwise injection |
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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:123 ; year:2016 ; pages:181-187 ; extent:7 |
| Links: |
|---|
| DOI / URN: |
10.1016/j.actaastro.2016.03.008 |
|---|
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ELV039942929 |
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| 520 | |a In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. | ||
| 520 | |a In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. | ||
| 650 | 7 | |a Cavity direct spanwise injection |2 Elsevier | |
| 650 | 7 | |a Ignition scheme |2 Elsevier | |
| 650 | 7 | |a Cavity upstream transverse injection |2 Elsevier | |
| 650 | 7 | |a Rearwall-expansion cavity |2 Elsevier | |
| 700 | 1 | |a Yang, Yixin |4 oth | |
| 700 | 1 | |a Sun, Mingbo |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.2016.03.008 doi GBVA2016002000004.pica (DE-627)ELV039942929 (ELSEVIER)S0094-5765(16)30079-0 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 a supersonic combustor with the rearwall-expansion cavity 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. Cavity direct spanwise injection Elsevier Ignition scheme Elsevier Cavity upstream transverse injection Elsevier Rearwall-expansion cavity Elsevier Yang, Yixin oth Sun, Mingbo 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:123 year:2016 pages:181-187 extent:7 https://doi.org/10.1016/j.actaastro.2016.03.008 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 123 2016 181-187 7 045F 520 |
| spelling |
10.1016/j.actaastro.2016.03.008 doi GBVA2016002000004.pica (DE-627)ELV039942929 (ELSEVIER)S0094-5765(16)30079-0 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 a supersonic combustor with the rearwall-expansion cavity 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. Cavity direct spanwise injection Elsevier Ignition scheme Elsevier Cavity upstream transverse injection Elsevier Rearwall-expansion cavity Elsevier Yang, Yixin oth Sun, Mingbo 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:123 year:2016 pages:181-187 extent:7 https://doi.org/10.1016/j.actaastro.2016.03.008 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 123 2016 181-187 7 045F 520 |
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10.1016/j.actaastro.2016.03.008 doi GBVA2016002000004.pica (DE-627)ELV039942929 (ELSEVIER)S0094-5765(16)30079-0 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 a supersonic combustor with the rearwall-expansion cavity 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. Cavity direct spanwise injection Elsevier Ignition scheme Elsevier Cavity upstream transverse injection Elsevier Rearwall-expansion cavity Elsevier Yang, Yixin oth Sun, Mingbo 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:123 year:2016 pages:181-187 extent:7 https://doi.org/10.1016/j.actaastro.2016.03.008 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 123 2016 181-187 7 045F 520 |
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10.1016/j.actaastro.2016.03.008 doi GBVA2016002000004.pica (DE-627)ELV039942929 (ELSEVIER)S0094-5765(16)30079-0 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 a supersonic combustor with the rearwall-expansion cavity 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. Cavity direct spanwise injection Elsevier Ignition scheme Elsevier Cavity upstream transverse injection Elsevier Rearwall-expansion cavity Elsevier Yang, Yixin oth Sun, Mingbo 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:123 year:2016 pages:181-187 extent:7 https://doi.org/10.1016/j.actaastro.2016.03.008 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 123 2016 181-187 7 045F 520 |
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10.1016/j.actaastro.2016.03.008 doi GBVA2016002000004.pica (DE-627)ELV039942929 (ELSEVIER)S0094-5765(16)30079-0 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 a supersonic combustor with the rearwall-expansion cavity 2016transfer abstract 7 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. Cavity direct spanwise injection Elsevier Ignition scheme Elsevier Cavity upstream transverse injection Elsevier Rearwall-expansion cavity Elsevier Yang, Yixin oth Sun, Mingbo 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:123 year:2016 pages:181-187 extent:7 https://doi.org/10.1016/j.actaastro.2016.03.008 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 123 2016 181-187 7 045F 520 |
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experimental investigation on ignition schemes of a supersonic combustor with the rearwall-expansion cavity |
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Experimental investigation on ignition schemes of a supersonic combustor with the rearwall-expansion cavity |
| abstract |
In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. |
| abstractGer |
In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. |
| abstract_unstemmed |
In this study, ignition schemes of the rearwall-expansion cavity in a model scramjet combustor were investigated under inflow conditions of Ma=2.52 with stagnation pressure P 0=1.6Mpa and stagnation temperature T 0=1486K. It is concluded that under the current experimental condition, it is necessary to apply combined injection setups to achieve a successful ignition process for the rearwall-expansion cavity, including the cavity upstream transverse injection and direct spanwise injection setups. Compared with the cavity direct injection on the rear wall, the cavity direct injection on the leading edge is more beneficial for the formation and propagation of the initial flame and it will performs a more robust combustion in the combustor. For the rearwall-expansion cavity, the combined injection (cavity upstream transverse injection and cavity direct spanwise injection on the leading edge) is an optimized injection setup during the ignition and flame stabilization processes. Due to the configuration characteristics of rearwall-expansion cavity, the wall-pressure distribution in the isolator will not be affected substantially by the heat release in the combustor during a robust combustion process, which is important for the prevention of thermal choking and the unstart of scramjet inlet. |
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Experimental investigation on ignition schemes of a supersonic combustor with the rearwall-expansion cavity |
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