Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor
The showerhead is the most common type of injector used in hybrid rocket motors due to its design and manufacture simplicity. The main drawback of the showerheads (SH) is the relatively low performance in terms of combustion efficiency because of the poor atomization of the liquid oxidizer. This stu...
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| Format: | Article |
| Language: | English |
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KeAi Communications Co. Ltd.
2021-12-01
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| Series: | FirePhysChem |
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| Online Access: | http://www.sciencedirect.com/science/article/pii/S2667134421000584 |
| _version_ | 1797976415087362048 |
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| author | M. Bouziane A.E.M. Bertoldi P. Hendrick M. Lefebvre |
| author_facet | M. Bouziane A.E.M. Bertoldi P. Hendrick M. Lefebvre |
| author_sort | M. Bouziane |
| collection | DOAJ |
| description | The showerhead is the most common type of injector used in hybrid rocket motors due to its design and manufacture simplicity. The main drawback of the showerheads (SH) is the relatively low performance in terms of combustion efficiency because of the poor atomization of the liquid oxidizer. This study investigates the problem to enrich the technical literature by presenting detailed experimental data on showerhead injectors by a series of static firing tests using a 1-kN lab-scale hybrid rocket, applying four kinds of showerhead injectors, named SH1 (benchmark), SH2, SH3, and SH4. They differ from each other by the number, distribution, and dimension of the orifice elements. Main performance parameters such as fuel regression rate, specific impulse, and combustion efficiency are experimentally obtained.Two different series of tests were carried out. At first, the influence of SH injector geometries was studied. The injectors SH2, SH3, and SH4 were used under the same initial conditions, and the results were compared with SH1. In the second set of tests, the SH4 injector was chosen, and the effects of the fuel grain initial port diameter were investigated. Using the data obtained in the second battery of tests was possible to determine the influence of the fuel port diameter on the motor efficiency and establish the regression rate law of nitrous oxidizer/paraffin-based fuel for this specific configuration. |
| first_indexed | 2024-04-11T04:50:34Z |
| format | Article |
| id | doaj.art-f2a94d9e333f4c01b0f2fc96261da4c5 |
| institution | Directory Open Access Journal |
| issn | 2667-1344 |
| language | English |
| last_indexed | 2024-04-11T04:50:34Z |
| publishDate | 2021-12-01 |
| publisher | KeAi Communications Co. Ltd. |
| record_format | Article |
| series | FirePhysChem |
| spelling | doaj.art-f2a94d9e333f4c01b0f2fc96261da4c52022-12-27T04:40:48ZengKeAi Communications Co. Ltd.FirePhysChem2667-13442021-12-0114231243Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motorM. Bouziane0A.E.M. Bertoldi1P. Hendrick2M. Lefebvre3Laboratory of propulsion and reactive system, Ecole Militaire Polytechnique, BP 17 Bordj-El-Bahri, Alger, Algiers; Corresponding author.Faculty of Gama, University of Brasília, Área Especial de Indústria e Projeção A, 72444-240 Brasília, BrazilAero-Thermo-Mechanics department, Université Libre de Bruxelles, F.D. Roosevelt Avenue 50, 1050 Brussels, BelgiumDepartment of Chemistry, Royal Military Academy, Avenue de la Renaissance 30, 1000 Brussels, BelgiumThe showerhead is the most common type of injector used in hybrid rocket motors due to its design and manufacture simplicity. The main drawback of the showerheads (SH) is the relatively low performance in terms of combustion efficiency because of the poor atomization of the liquid oxidizer. This study investigates the problem to enrich the technical literature by presenting detailed experimental data on showerhead injectors by a series of static firing tests using a 1-kN lab-scale hybrid rocket, applying four kinds of showerhead injectors, named SH1 (benchmark), SH2, SH3, and SH4. They differ from each other by the number, distribution, and dimension of the orifice elements. Main performance parameters such as fuel regression rate, specific impulse, and combustion efficiency are experimentally obtained.Two different series of tests were carried out. At first, the influence of SH injector geometries was studied. The injectors SH2, SH3, and SH4 were used under the same initial conditions, and the results were compared with SH1. In the second set of tests, the SH4 injector was chosen, and the effects of the fuel grain initial port diameter were investigated. Using the data obtained in the second battery of tests was possible to determine the influence of the fuel port diameter on the motor efficiency and establish the regression rate law of nitrous oxidizer/paraffin-based fuel for this specific configuration.http://www.sciencedirect.com/science/article/pii/S2667134421000584Hybrid rocket motorsInjector designAxial injectionRegression rateInitial port fuel grain diameterExhaust plume |
| spellingShingle | M. Bouziane A.E.M. Bertoldi P. Hendrick M. Lefebvre Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor FirePhysChem Hybrid rocket motors Injector design Axial injection Regression rate Initial port fuel grain diameter Exhaust plume |
| title | Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor |
| title_full | Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor |
| title_fullStr | Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor |
| title_full_unstemmed | Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor |
| title_short | Experimental investigation of the axial oxidizer injectors geometry on a 1-kN paraffin-fueled hybrid rocket motor |
| title_sort | experimental investigation of the axial oxidizer injectors geometry on a 1 kn paraffin fueled hybrid rocket motor |
| topic | Hybrid rocket motors Injector design Axial injection Regression rate Initial port fuel grain diameter Exhaust plume |
| url | http://www.sciencedirect.com/science/article/pii/S2667134421000584 |
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