Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity
Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environm...
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MDPI AG
2019-03-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/12/7/1235 |
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| author | Chaolong Li Zhixun Xia Likun Ma Xiang Zhao Binbin Chen |
| author_facet | Chaolong Li Zhixun Xia Likun Ma Xiang Zhao Binbin Chen |
| author_sort | Chaolong Li |
| collection | DOAJ |
| description | Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) <inline-formula> <math display="inline"> <semantics> <mrow> <mi>k</mi> <mo>−</mo> <mi>ω</mi> </mrow> </semantics> </math> </inline-formula> turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor. |
| first_indexed | 2024-04-14T00:52:01Z |
| format | Article |
| id | doaj.art-b5f529405fa64875a3992c9503add096 |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-04-14T00:52:01Z |
| publishDate | 2019-03-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-b5f529405fa64875a3992c9503add0962022-12-22T02:21:45ZengMDPI AGEnergies1996-10732019-03-01127123510.3390/en12071235en12071235Numerical Study on the Solid Fuel Rocket Scramjet Combustor with CavityChaolong Li0Zhixun Xia1Likun Ma2Xiang Zhao3Binbin Chen4Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, ChinaScience and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, ChinaScience and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, ChinaScience and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, ChinaScience and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, ChinaScramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) <inline-formula> <math display="inline"> <semantics> <mrow> <mi>k</mi> <mo>−</mo> <mi>ω</mi> </mrow> </semantics> </math> </inline-formula> turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor.https://www.mdpi.com/1996-1073/12/7/1235solid-fuel rocket scramjet (SFRSCRJ)cavitysupersonic combustioncombustor performanceparticle combustion |
| spellingShingle | Chaolong Li Zhixun Xia Likun Ma Xiang Zhao Binbin Chen Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity Energies solid-fuel rocket scramjet (SFRSCRJ) cavity supersonic combustion combustor performance particle combustion |
| title | Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity |
| title_full | Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity |
| title_fullStr | Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity |
| title_full_unstemmed | Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity |
| title_short | Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity |
| title_sort | numerical study on the solid fuel rocket scramjet combustor with cavity |
| topic | solid-fuel rocket scramjet (SFRSCRJ) cavity supersonic combustion combustor performance particle combustion |
| url | https://www.mdpi.com/1996-1073/12/7/1235 |
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