Prospects for scramjet engines in reusable launch applications: A review

Sam, Lissen; Idithsaj, P.T.; Nair, Prasanth P.; Suryan, Abhilash; Narayanan, Vinod

doi:10.1016/j.ijhydene.2023.05.341

Cited by 25 publications

(2 citation statements)

References 180 publications

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“…Scramjet engines have the advantages of a simple structure (as shown in Figure 1), light weight, a high specific impulse, fast speed, and the ability to replenish oxygen without the need to carry it with them [1,2]. They have been widely used in fields such as space shuttles, high-speed weapons, and wide-speed-range vehicles [3], and comprise one of the most efficient and promising propulsion systems [4][5][6]. When a scramjet engine operates normally, air enters the engine at extremely high speeds, and the time for fuel injection, fuel/air mixing, and combustion in the combustion chamber is only a few milliseconds [7].…”

Section: Introductionmentioning

confidence: 99%

Parametric Study of Flow and Combustion Characteristic in a Cavitied Scramjet with Multi-Position Injection

Xi,

Liu,

Shao

et al. 2024

Fire

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This study focuses on the three-dimensional flow and combustion characteristics of a cavitied scramjet engine with multi-position injection. A single-equation large eddy simulation (LES) turbulence model is employed, with a detailed reaction mechanism for hydrogen combustion, as described by Jachimowski. The combustion characteristics of hydrogen in the scramjet combustion chamber are analyzed. Based on the combustion chamber model, the influence of different equivalence ratios, injection timing, injection positions, and injection pressures on the flame formation and propagation process are compared. The results indicate that within a certain range, an increase in the equivalence ratio enhances the combustion intensity and chamber pressure. In the case of multi-position injection, the order of injection from different nozzles has little effect on the final flame stabilization mode and pressure distribution. The opposite-side distribution of nozzles can effectively improve the fuel efficiency and the internal pressure. Furthermore, when the nozzles are closely placed in the opposite-side distribution, the combustion efficiency increases, although this leads to a higher total pressure loss. In scenarios where the fuel injection duration is short, an increase in the injection pressure at the upstream nozzles of the cavity results in a higher local equivalence ratio, as well as reduced fuel mixing and ignition time.

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Section: Introductionmentioning

confidence: 99%

Parametric Study of Flow and Combustion Characteristic in a Cavitied Scramjet with Multi-Position Injection

Xi,

Liu,

Shao

et al. 2024

Fire

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“…With the continuous development of the Rotating Detonation Engine (RDE), the demand for high-temperature resistance, especially ablation resistance, of combustion chambers and nozzles is also increasing [1][2][3][4]. Ceramic matrix composites (CMCs) are widely regarded as the most promising thermal protection materials due to their excellent high-temperature resistance, oxidation resistance, and ablation resistance [5,6].…”

Section: Introductionmentioning

confidence: 99%

Cyclic Ablation Properties of C/SiC-ZrC Composites

Ge,

Zhang,

Zhang

et al. 2024

Aerospace

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To reveal the ablation performance of C/SiC-ZrC composites under different ablation modes, C/SiC-ZrC composites were prepared using chemical vapor deposition, precursor infiltration, and pyrolysis. Single ablation and cyclic ablation tests were conducted on the C/SiC-ZrC composites using an oxyacetylene flame, in order to obtain ablation parameters, as well as macroscopic and microscopic ablation morphology for the different ablation modes. The results show that the linear ablation rate and mass ablation rate of different ablation modes decrease with increasing time. The linear ablation rate and mass ablation rate of cyclic ablation are 12% and 24.2% lower than those of single ablation. Within the same ablation time, the C/SiC-ZrC composites subjected to cyclic ablation exhibit shallower and more evenly distributed pits, caused by high-temperature airflow ablation. The material surface has a white oxide layer composed of SiO2 and ZrO2, and the carbon fibers inside are wrapped by oxide particles, enhancing the ablation resistance of C/SiC-ZrC composites.

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