Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism
| Publication Date: |
2018-03-12
|
|---|---|
| Publisher: |
Hindawi
|
| Print ISSN: |
1687-5966
|
| Electronic ISSN: |
1687-5974
|
| Topics: |
Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
|
| Published by: |
| _version_ | 1836398840754733057 |
|---|---|
| autor | A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen |
| beschreibung | A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground Isp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6~0.8 mm/s at the surface of disk walls and 1.5~1.7 mm/s at the surface of central core of the fuel grain. |
| citation_standardnr | 6202594 |
| datenlieferant | ipn_articles |
| feed_id | 97414 |
| feed_publisher | Hindawi |
| feed_publisher_url | http://www.hindawi.com/ |
| insertion_date | 2018-03-12 |
| journaleissn | 1687-5974 |
| journalissn | 1687-5966 |
| publikationsjahr_anzeige | 2018 |
| publikationsjahr_facette | 2018 |
| publikationsjahr_intervall | 7984:2015-2019 |
| publikationsjahr_sort | 2018 |
| publisher | Hindawi |
| quelle | International Journal of Aerospace Engineering |
| relation | http://www.hindawi.com/journals/ijae/2018/6513084/ |
| search_space | articles |
| shingle_author_1 | A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen |
| shingle_author_2 | A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen |
| shingle_author_3 | A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen |
| shingle_author_4 | A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen |
| shingle_catch_all_1 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground Isp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6~0.8 mm/s at the surface of disk walls and 1.5~1.7 mm/s at the surface of central core of the fuel grain. A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen Hindawi 1687-5966 16875966 1687-5974 16875974 |
| shingle_catch_all_2 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground Isp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6~0.8 mm/s at the surface of disk walls and 1.5~1.7 mm/s at the surface of central core of the fuel grain. A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen Hindawi 1687-5966 16875966 1687-5974 16875974 |
| shingle_catch_all_3 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground Isp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6~0.8 mm/s at the surface of disk walls and 1.5~1.7 mm/s at the surface of central core of the fuel grain. A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen Hindawi 1687-5966 16875966 1687-5974 16875974 |
| shingle_catch_all_4 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground Isp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6~0.8 mm/s at the surface of disk walls and 1.5~1.7 mm/s at the surface of central core of the fuel grain. A. Lai, T.-H. Chou, S.-S. Wei, J.-W. Lin, J.-S. Wu, and Y.-S. Chen Hindawi 1687-5966 16875966 1687-5974 16875974 |
| shingle_title_1 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism |
| shingle_title_2 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism |
| shingle_title_3 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism |
| shingle_title_4 | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism |
| timestamp | 2025-06-30T23:33:28.454Z |
| titel | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism |
| titel_suche | Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism |
| topic | ZL |
| uid | ipn_articles_6202594 |