Combustion Characteristics in Rotating Detonation Engines
A lot of studies on rotating detonation engines have been carried out due to the higher thermal efficiency. However, the number, rotating directions, and intensities of rotating detonation waves are changeful when the flow rate, equivalence ratio, inflow conditions, and engine schemes vary. The pres...
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| Format: | Article |
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Wiley
2021-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2021/8839967 |
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| author | Yuhui Wang Wenyou Qiao JialingLe |
| author_facet | Yuhui Wang Wenyou Qiao JialingLe |
| author_sort | Yuhui Wang |
| collection | DOAJ |
| description | A lot of studies on rotating detonation engines have been carried out due to the higher thermal efficiency. However, the number, rotating directions, and intensities of rotating detonation waves are changeful when the flow rate, equivalence ratio, inflow conditions, and engine schemes vary. The present experimental results showed that the combustion mode of a rotating detonation engine was influenced by the combustor scheme. The annular detonation channel had an outer diameter of 100 mm and an inner diameter of 80 mm. Air and hydrogen were injected into the combustor from 60 cylindrical orifices in a diameter of 2 mm and a circular channel with a width of 2 mm, respectively. When the air mass flow rate was increased by keeping hydrogen flow rate constant, the combustion mode varied. Deflagration and diffusive combustion, multiple counterrotating detonation waves, longitudinal pulsed detonation, and a single rotating detonation wave occurred. Both longitudinal pulsed detonation and a single rotating detonation wave occurred at different times in the same operation. They could change between each other, and the evolution direction depended on the air flow rate. The operations with a single rotating detonation wave occurred at equivalence ratios lower than 0.60, which was helpful for the engine cooling and infrared stealth. The generation mechanism of longitudinal pulsed detonation is developed. |
| format | Article |
| id | doaj-art-a777536c82bc4922b73d1e32f6f0f866 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2021-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-a777536c82bc4922b73d1e32f6f0f8662025-02-03T01:29:19ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742021-01-01202110.1155/2021/88399678839967Combustion Characteristics in Rotating Detonation EnginesYuhui Wang0Wenyou Qiao1JialingLe2College of Mechanical and Electrical Engineering, Beijing University of Chemical Technology, Beijing, ChinaSouthwest University of Science and Technology, Mianyang, ChinaChina Aerodynamics Research and Development Center, Mianyang, ChinaA lot of studies on rotating detonation engines have been carried out due to the higher thermal efficiency. However, the number, rotating directions, and intensities of rotating detonation waves are changeful when the flow rate, equivalence ratio, inflow conditions, and engine schemes vary. The present experimental results showed that the combustion mode of a rotating detonation engine was influenced by the combustor scheme. The annular detonation channel had an outer diameter of 100 mm and an inner diameter of 80 mm. Air and hydrogen were injected into the combustor from 60 cylindrical orifices in a diameter of 2 mm and a circular channel with a width of 2 mm, respectively. When the air mass flow rate was increased by keeping hydrogen flow rate constant, the combustion mode varied. Deflagration and diffusive combustion, multiple counterrotating detonation waves, longitudinal pulsed detonation, and a single rotating detonation wave occurred. Both longitudinal pulsed detonation and a single rotating detonation wave occurred at different times in the same operation. They could change between each other, and the evolution direction depended on the air flow rate. The operations with a single rotating detonation wave occurred at equivalence ratios lower than 0.60, which was helpful for the engine cooling and infrared stealth. The generation mechanism of longitudinal pulsed detonation is developed.http://dx.doi.org/10.1155/2021/8839967 |
| spellingShingle | Yuhui Wang Wenyou Qiao JialingLe Combustion Characteristics in Rotating Detonation Engines International Journal of Aerospace Engineering |
| title | Combustion Characteristics in Rotating Detonation Engines |
| title_full | Combustion Characteristics in Rotating Detonation Engines |
| title_fullStr | Combustion Characteristics in Rotating Detonation Engines |
| title_full_unstemmed | Combustion Characteristics in Rotating Detonation Engines |
| title_short | Combustion Characteristics in Rotating Detonation Engines |
| title_sort | combustion characteristics in rotating detonation engines |
| url | http://dx.doi.org/10.1155/2021/8839967 |
| work_keys_str_mv | AT yuhuiwang combustioncharacteristicsinrotatingdetonationengines AT wenyouqiao combustioncharacteristicsinrotatingdetonationengines AT jialingle combustioncharacteristicsinrotatingdetonationengines |