Numerical Investigation of Self-Ignition Characteristics of Solid-Fuel Scramjet Combustor

Chi, Hongwei; Wei, Zhijun; Wang, Li-he; Li, Biao; Wu, Zhiwen

doi:10.2514/1.b35301

Cited by 21 publications

(8 citation statements)

References 30 publications

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“…Computational and numerical studies provide some additional confirmation on the functionality of SFSJs [80,81,82,83,84]. Many of the more recent numerical studies have been conducted at the Beijing Institute of Technology.…”

Section: Solid Fuel Scramjetmentioning

confidence: 91%

Supersonic Combustion of Solid Fuels

Schlussel,

Gallegos,

Young

2024

Journal of Propulsion and Power

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Supersonic combustion of solid fuels is investigated experimentally using a rectangular-cross-section combustor in the context of understanding ignition characteristics, studying fuel regression, and determining operating conditions. Fuel grains consisted of 3D printed polymethyl-methacrylate of varying geometry. Specifically, the cavity flameholder dimensions are systematically studied to develop a flammability map. Initial examinations reveal that a longer and larger cross-sectional area of the flameholding zone in the fuel grain creates the most optimal conditions for ignition and sustained flameholding. The longer and larger flameholding zone also creates conditions for faster time-averaged regression rates. The ignition characteristics and fuel regression are also examined by varying inlet temperatures of the air, which showed that a higher inlet temperature is conducive to sustained ignition, as well as higher fuel regression rates. This work extends the available literature on supersonic combustion of solid fuels to lower temperatures than has previously been reported.

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Section: Solid Fuel Scramjetmentioning

confidence: 91%

Supersonic Combustion of Solid Fuels

Schlussel,

Gallegos,

Young

2024

Journal of Propulsion and Power

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“…So far, there are three types of the typical structures of scramjet combustor, i.e., the cavity- [2,3,[6][7][8][9][10][11][12][13][14][15], strut- [5,16], and backward-facing step-based combustor [4,[17][18][19][20]. The strut-based combustor was first proposed by Waidmann et al [21]; they used hydrogen as the fuel to investigate the combustion characteristic of a typical strut-based scramjet combustor (DLR (German Aerospace Center) scramjet) via experimental approach; in this investigation, the flow features were clearly captured, and the chamber pressure was found to be enhanced with increasing of hydrogen mass flow rate.…”

Section: Introductionmentioning

confidence: 99%

A Preliminary Research on Combustion Characteristics of a Novel-Type Scramjet Combustor

Zhang

Chang

Cai

et al. 2022

International Journal of Aerospace Engineering

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In this work, a new configuration of strut-based scramjet is proposed, and a series of simulations are conducted to investigate its possibility of practical application. The simulation results are verified via the classical DLR ramjet and an experiment conducted on the connected pipe facility. The inlet area ( A in ) and air intake height ( H ) of the combustor are varied independently to investigate their performance. The results indicate that the flow field and shock wave structure of such engine reveal similar characteristics as the classical DLR engine, and the variation in engine geometry can significantly affect its combustion characteristics. Moreover, the combustion efficiency could be enhanced by 2% as the A in varied from 900π mm2 to 1100π mm2; increasing the air intake path ( H ) to 12 mm can increase the combustion efficiency by 25%. In general, the present work proposes a new geometry of the scramjet combustor; this combustor has possibility of practical application, but a further and detailed investigation is still needed.

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“…Powered hypersonic flight (Ma > 5) is currently a research hotspot in the field of aerospace, with the scramjet being an ideal propulsion equipment for this purpose [1][2][3][4]. While most of the current research is based on liquid fuels, the scramjet that employs solid fuel (SSRJ) has many advantages, including simple structure, high energy density, low cost, and safety [5][6][7][8]. Due to this, the SSRJ has become one of the most promising engine types for hypersonic future vehicles.…”

Section: Introductionmentioning

confidence: 99%

Direct-Connect Test of Solid Scramjet with Symmetrical Structure

Yang

Xia

et al. 2021

Energies

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The solid scramjet has become one of the most promising engine types. In this paper, we report the first direct-connect test of a solid scramjet with symmetrical structure, carried out using boron-based fuel-rich solid propellant as fuel. During the test, which simulated a flight environment at Mach 5.6 and 25 km, the performance of the solid scramjet was obtained by measuring the pressure, thrust, and mass flow. The results show that, due to the change in the combustion area of the propellant and the deposition of the throat in the gas generator during the test, the equivalence ratio gradually increased from 0.54 to 0.63. In a solid scramjet, it is possible to obtain a symmetrical distribution of the flow field within the combustor. Moreover, in a multi-cavity combustor, the combustion state expands from the cavity to the center of the flow channel. The performance of the solid scramjet increased during the test, reaching a combustion efficiency of about 42%, a total pressure recovery coefficient of 0.35, and a thrust gain specific impulse of about 418 s. The solid scramjet with symmetrical structure is feasible. The cavity configuration adopted in this paper can reduce the ignition delay time of fuel-rich gas and improve the combustion efficiency of gas-phase combustible components. The shock trains in the isolator are conducive to the recovery of the total pressure. The performance of the solid scramjet is limited by the low combustion efficiency of the particles.

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Numerical Investigation of Self-Ignition Characteristics of Solid-Fuel Scramjet Combustor

Cited by 21 publications

References 30 publications

Supersonic Combustion of Solid Fuels

Supersonic Combustion of Solid Fuels

A Preliminary Research on Combustion Characteristics of a Novel-Type Scramjet Combustor

Direct-Connect Test of Solid Scramjet with Symmetrical Structure

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