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