A review of aircraft subsonic and supersonic combustors

Abdulrahman, Gubran A.Q.; Qasem, Naef A.A.; Abdallah, Ayman M.; Habib, Mohamed A.

doi:10.1016/j.ast.2022.108067

Cited by 32 publications

(6 citation statements)

References 316 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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“…One of the significant features of the scramjet is that the supersonic flow conditions in the combustor lead to very short residence times for fuel and air, typically of the order of milliseconds; therefore, the fuel must mix with the supersonic air flow and burn entirely within a short time. Thus, future hypersonic propulsion systems' success will largely depend on efficient injection, mixing, and combustion processes inside the supersonic combustion chamber [1,3].…”

Section: Introductionmentioning

confidence: 99%

“…These conditions can significantly alter chemical kinetics and reaction rates, leading to different reaction pathways and species formation compared to subsonic conditions. Ignition and flame stabilization processes in supersonic combustion devices may differ significantly from those observed in the subsonic regime [3]. Furthermore, turbulence increases the mixing of fuel and oxidizer and enhances combustion [20].…”

Section: Introductionmentioning

confidence: 99%

Development and Validation of a Compressible Reacting Gas-Dynamic Flow Solver for Supersonic Combustion

Gilmanov,

Gokulakrishnan,

Klassen

2024

Dynamics

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An approach based on the OpenFOAM library has been developed to solve a high-speed, multicomponent mixture of a reacting, compressible flow. This work presents comprehensive validation of the newly developed solver, called compressibleCentralReactingFoam, with different supersonic flows, including shocks, expansion waves, and turbulence–combustion interaction. The comparisons of the simulation results with experimental and computational data confirm the fidelity of this solver for problems involving multicomponent high-speed reactive flows. The gas dynamics of turbulence–chemistry interaction are modeled using a partially stirred reactor formulation and provide promising results to better understand the complex physics involved in supersonic combustors. A time-scale analysis based on local Damköhler numbers reveals different regimes of turbulent combustion. In the core of the jet flow, the Damköhler number is relatively high, indicating that the reaction time scale is smaller than the turbulent mixing time scale. This means that the combustion is controlled by turbulent mixing. In the shear layer, where the heat release rate and the scalar dissipation rate have the highest value, the flame is stabilized due to finite rate chemistry with small Damköhler numbers and a limited fraction of fine structure. This solver allows three-dimensional gas dynamic simulation of high-speed multicomponent reactive flows relevant to practical combustion applications.

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“…One of the significant features of the scramjet is the supersonic flow conditions in the combustor lead to very short residence times for fuel and air, typically of the order of milliseconds; therefore, the fuel must mix with the supersonic flow and burn entirely within a short time. Thus, future hypersonic propulsion systems' success will largely depend on efficient injection, mixing, and combustion processes inside the supersonic combustion chamber [1,3].…”

Section: Introductionmentioning

confidence: 99%

“…These conditions can significantly alter chemical kinetics and reaction rates, leading to different reaction pathways and species formation compared to subsonic conditions. Ignition and flame stabilization processes in supersonic combustion devices may differ significantly from those observed in the subsonic regime [3]. Combustion processes involve highly nonlinear chemical reactions and many species.…”

Section: Introductionmentioning

confidence: 99%

Development and Validation of a Compressible Reacting Gas-Dynamic Flow Solver for Supersonic Combustion

Gilmanov,

Gokulakrishnan,

Klassen

2023

Preprint

View full text Add to dashboard Cite

An approach based on the OpenFOAM library has been developed to solve a high-speed, multicomponent mixture of a reacting, compressible flow. This work presents comprehensive validation of the newly developed solver called compressibleCentralReactingFoam with different supersonic flows, including shocks, expansion waves, and turbulence-combustion interaction. The comparisons of the simulation results with experimental and computational data confirm the fidelity of this solver for problems involving multicomponent high-speed reactive flows. The gas dynamics of turbulence-chemistry interaction are modeled using a partially-stirred reactor formulation and provide promising results to better understand the complex physics involved in supersonic combustors. A time-scale analysis based on local Damköhler numbers reveals different regimes of turbulent combustion. In the core of the jet flow, the Damköhler number is relatively high indicating that the reaction time scale is smaller than the turbulent mixing time scale. This means that the combustion is controlled by turbulent mixing. In the shear layer, where the heat release rate and the scalar dissipation rate have the highest value, the flame is stabilized due to finite rate chemistry with small Damköhler numbers and a high fraction of fine structure. This solver allows three-dimensional gas dynamic simulation of high-speed multicomponent reactive flows relevant to practical combustion applications.

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A review of aircraft subsonic and supersonic combustors

Cited by 32 publications

References 316 publications

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

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

Development and Validation of a Compressible Reacting Gas-Dynamic Flow Solver for Supersonic Combustion

Development and Validation of a Compressible Reacting Gas-Dynamic Flow Solver for Supersonic Combustion

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