Characterization of kerosene distribution around the ignition cavity in a scramjet combustor

Li, Xipeng; Liu, Weidong; Pan, Yu; Yang, Leichao; An, Bin; Zhu, Jiajian

doi:10.1016/j.actaastro.2017.01.037

Cited by 60 publications

(9 citation statements)

References 19 publications

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“…Thus total pressure loss in a single-strut combustor is 14% lower than that of a combustor with a multi strut. [50][51][52][53][54][55][56][57][58][59][60]…”

Section: Discussionmentioning

confidence: 99%

“…51 The flow is considered to be ideal gas, and the thermal F I G U R E 1 Schematic layout of the 2D combustor model conductivity and viscosity are computed using mass-weighted-mixing law. 52 The Courant-Friedrichs-Lewy (CFL) number is chosen as 0.5 under the relevant relation factor to ensure stability. 53 The governing equations, that is, mass, momentum, and energy equations written for the total enthalpy, are expressed as follows:…”

Section: Numerical Flow Modeling and Simulationmentioning

confidence: 99%

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Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

2021

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This study aims at investigating the effect of a multistrut-based hydrogen injector in a scramjet combustor underreacting case. The numerical analysis is carried out using two-dimensional Reynolds-averaged Navier-Stokes equations with the Shear Stress Transport k − ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters, such as the shock wave pattern, wall pressures, and static temperature across the combustor, are validated with the reported experimental results. The results comply with the range, indicating that the adopted simulation method for single strut injection can be extended for other investigations. It is noticed that with multistrut injectors, as hydrogen jet pressure increases in the supersonic flow field, the jet penetration rate in the lateral direction of the flow and the total pressure loss as compared with the baseline injection pressure conditions has increased. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency, mixing efficiency, and total pressure loss. Compared with the single-strut output of a scramjet combustor, multistruts inclusion increased the combustion efficiency by almost 18%, the mixing efficiency attained the maximum with 16% fewer lengths. The total pressure loss in single-strut is 14% lower than that of multistrut.

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“…Thus total pressure loss in a single-strut combustor is 14% lower than that of a combustor with a multi strut. [50][51][52][53][54][55][56][57][58][59][60]…”

Section: Discussionmentioning

confidence: 99%

Section: Numerical Flow Modeling and Simulationmentioning

confidence: 99%

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

2021

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“…Li et al [31] studied the fuel distribution characteristics on kerosene-fueled scramjet combustor with a dual cavity to interpret the effect of ignition pressure for flight and entrance Mach numbers 5.5 and 2.5, respectively. e formation of the shear layer plays an important role in fuel distribution and engagement.…”

Section: Challenges In the Design Of Scramjet Enginesmentioning

confidence: 99%

Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor

Bordoloi

Pandey

Sharma

2021

Mathematical Problems in Engineering

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The air-breathing engines, commonly known as Supersonic Combustor Ramjet (SCRAMJET) engines, are one of the most prominent technologies among researchers due to their high thrust-to-weight ratio. The researchers are constantly making efforts for improved performance of the combustor under the required boundary conditions. The present working computational model studies a hydrogen-fueled parallel cavity scramjet combustor to recognize the complex flow field characteristics and performance of the combustor in Ansys 15.0. The computational model developed is a replica of an experiment conducted in China which slightly modified the boundary conditions. The standard two-equation K- ε turbulence model and Reynolds averaged Navier Stokes (RANS) equation with finite-rate/eddy dissipation species reaction model are used to simulate the problem. The validation of the present model is achieved by comparing the results with already available experimental data in conformity with the literature. The results of the simulations are in satisfactory accord with the experimental data and images. Furthermore, to achieve the stated objective, different incoming Mach numbers, namely, 2.25, 2.52, and 2.75, are considered for a more clear understanding of variables that affects the characteristics of the flow field. The temperature, Mach number, density pressure, and H2O mass fraction contours were studied to facilitate proper understanding. The maximum temperature rise observed is 2711.467 K for M = 2.25. Additionally, the performance parameters, namely, combustion and mixing efficiencies, are also studied. The maximum combustion and mixing efficiencies are 87.47% and 98.15% for M = 2.25 and 2.75, respectively.

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“…For spatial discretization, a second-order upwind system (SOU) is used along with the Advection Upstream Splitting Method (AUSM) flux splitting to provide an effective solution with reliable convergence characteristics. 22 To ensure stability, the Courant-Friedrichs-Levy (CFL) number is specified as 0.5, suggested by Choubey and Pandey. 23 The governing equations, that is, mass, momentum, and energy equations, can be found in the literature.…”

Section: Numerical Modelingmentioning

confidence: 99%

The non-reacting flow characteristics of pylon and wall injections in a dual combustion ramjet engine

Sebastin

Jeyakumar

Karthik

2021

International Journal of Engine Research

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The influence of pylon and wall injection in coaxial jets of a Dual Combustion Ramjet engine is numerically investigated in a non-reacting flow field. The supersonic combustor is modeled and analyzed using the commercial CFD software ANSYS 18.0. The three-dimensional compressible Reynolds-averaged Navier-Stokes (RANS) equations coupled with the SST k-ω turbulence model have been used to analyze the coaxial mixing characteristics of the jets. The numerical study is validated with the experimental data of the wall static pressures measured in the combustor’s flow direction. The pylon and wall injectors are located symmetrically at the gas generator’s exit nozzle, and the air is used as the injectant to simulate gaseous fuel. Three injection pressures are used for the study to understand the flow field characteristics in the injector regime. Also, the gas generator downstream direction is investigated. The shock waves generated from the gas generator nozzle enhance the mixing of the coaxial jets with minimum total pressure loss. The shock wave interactions are noticed with reducing intensity within the supersonic combustor for pylon injection, leading to higher total pressure loss than the wall injection. The pylon injection provides the spatial distribution of fuels compared to the wall injection in the coaxial supersonic flow field.

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Characterization of kerosene distribution around the ignition cavity in a scramjet combustor

Cited by 60 publications

References 19 publications

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor

The non-reacting flow characteristics of pylon and wall injections in a dual combustion ramjet engine

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