Quasi-one-dimensional model of supersonic a combustor with various fuels
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A computationally efficient quasi-one-dimensional model is needed to facilitate designs of scramjet engines.A universal quasi-one-dimensional hypersonic propulsion model was developed which is applicable to both gas and liquid hydrocarbon fueled scramjets with isolators and transonic flow.Euler equations are used to analyze the effects of combustor cross sectional area variation,evaporation of liquid fuels,fuel mass addition,friction and the oblique shock train in the isolator.The model was evaluated against three scramjet experiments with various fuels,the hydrogen-fueled NAL dual-mode scramjet,a supercritical kerosene-fueled scramjet and a liquid kerosene-fueled scramjet.The effectiveness and accuracy of the model were validated by good agreement between the predictions and experimental data.Thus,this scramjet propulsion model can be used for configuration design and parameter optimization with different kinds of fuels.Keywords:
Scramjet
Isolator
Ramjet
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Scramjet
Ramjet
Rocket (weapon)
Hypersonic flight
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Computational-fluid-dynamics-based design and analysis is presented for a full-scale scramjet combustor with kerosene fuel injected from struts placed in the combustor flowpath. Three-dimensional Navier-Stokes equations are solved with a K-e turbulence model using commercial computational-fluid-dynamics software. Combustion is modeled based on infinitely fast chemical kinetics. Lagrangian dispersed-phase analysis is considered for fueldroplet evaporation and mixing in the supersonic stream. Parametric studies are carried out to investigate the effect of combustor-inlet Mach number and total pressure on the flow development process. A higher combustor-entry Mach number and distributed-fuel-injection system will ensure the existence of predominant supersonic flow in the combustor. Simulations are also carried out to investigate two different kinds of fuel injection struts in the scramjet combustor performance. A distributed-fuel -injection system, required to avoid thermal choking, increases the three-dimensionality of the flowfield.
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To study and design actively-cooled scramjet,an iterative analysis and design method has been developed to study the coupling processes of combustion and heat transfer in an actively-cooled scramjet combustor. The method uses the measured static pressure distribution along the combustor as the input of an integrated thermal analysis code to calculate the fuel properties after cooling,which in turn are used as the fuel conditions for a direct-connected combustion test to obtain the updated static combustion pressure. This process continues until the fuel state no long varies and the final values of the characteristics of combustion and heat transfer in the actively-cooled scramjet combustor could be determined. Following the approach,the states of a close-loop-cooled scramjet combustor were studied for conditions corresponding to different flight Mach numbers and the cooling fuel temperature and structure temperature distribution at different flight Mach numbers were obtained.
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The scramjet thermal environment was studied in this paper.The computational model for the scramjet thermal environment was established based on the two-dimensional N-S equation and one-dimensional Raleigh heating law.The simulation program was developed using MacCormark forecast-calibration scheme.Thermal environment of the scramjet with Mach 6 and Mach 8 was computed,the scramjet internal flow field temperature and wall heat flux distribution were gained.The analysis of the results shows that the combination of 2D no reaction flow field calculation and 1D heating law of the thermal environment research of scramjets are feasible and effective.
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*† ‡ § This paper presents the application of the CIRA 3D code C3NS to the simulation of supersonic combustion problems typical of scramjet engines. After a brief code description, a trade-off analysis, carried out in order to find a reduced kinetic mechanism for Air-H2 combustion, is presented. The selected mechanism has to be computationally not heavy but, at the same time, accurate in the prediction of ignition delay time and adiabatic flame temperature. Furthermore, 2D and 3D flow problems reproducing supersonic mixing and combustion processes have been investigated with the purpose of obtaining a verification of the implemented models and a validation by comparing numerical and available experimental data. In particular, three tests of growing complexity, representative of typical supersonic combustion configuration have been selected. The first one is a typical validation tests of mixing and combustion in a parallel-injection configuration (TC-1). The last two tests are typical scramjet engine applications: the TC-2 is a test case representative of a scramjet combustor and TC-3 is a scramjet wind tunnel model in fuel off and fuel on configuration. The results show a good agreement with experimental data and are encouraging in order to employ the code in more complex applications including the evaluation of propulsion systems performances.
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Scramjet
Solver
Ramjet
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Numerical investigation of flow phenomena in a scramjet combustor has been performed for different geometric and operating parameters. The present investigation aims to find the optimal geometric parameters for a better fuel injection system with maximum combustion efficiency. Two-dimensional unsteady equations governing the compressible, turbulent reacting flow are solved using a commercial CFD solver. A combination of eddy dissipation (ED) and finite rate chemistry (FRC) models are used to model the combustion. The effect of divergence angles and scaling on the performance of a scramjet combustor is reported here. The effect of shocks generated by the strut and inlet conditions of a scramjet combustor on combustion efficiency has been reported. Present results show that the divergence angle and inlet conditions of combustors have significant effects on performance. A multiple-strut combustor has shown higher efficiency than a single-strut combustor. The modifications that improved the combustion efficiency of a DLR combustor are reported. The present simulation results match well with the experimental results available from the literature.
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Ramjet
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On the basis of 3-D viscous, turbulent and reactive Navier-Stokes numerical equation, the finite-rate chemistry/eddy-dissipation model for modeling the turbulent combusion is established. The fluid dynamic mechanisms of the dual-mode scramjet combustor using hydrogen as the fuel is studied. The effects of the ratio of the air to fuel, fuel injection angle and flight Mach number on the dual-scramjet working mode are analyzed, and the function of the isolator is analyzed too.
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Isolator
Ramjet
Large-Eddy Simulation
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A quasi-one-dimensional combustor model is developed using MacCormack’s method to solve simplified Navier–Stokes equations for the intention of simulating the flow parameters in the combustor. The combustor model is capable of predicting the flowfield of scramjet combustor. The Eckert reference technique is adopted in the heat transfer model of the regenerative cooling system. With these two models, the relationships between phenomena are investigated. Simulation results indicate that this coupled model of combustor and regenerative cooling system can be used to investigate the influence of the cooling channel geometry, flight Mach number and fuel equivalence ratio. This coupled model is useful for the pre-design of scramjet engines.
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A computationally efficient, quasi-one-dimensional, supersonic combustion ramjet (scramjet) propulsion model has been produced for use in hypersonic system design studies. The model solves a series of ordinary differential equations using a fourth-order Runge–Kutta method to describe the gas dynamics within the scramjet duct. Additional models for skin friction and wall heat transfer are also included. The equations are derived assuming an open thermodynamic system with equilibrium or simplified-chemistry combustion models. The combustion is also assumed to be mixing-limited rather than kinetically limited. This assumption allows simplification of the modeling and is justified when the model is compared against experimental results. Three test cases are used to validate the performance of the scramjet propulsion model: 1) a reflected-shock-tunnel hydrogen-fueled scramjet experiment, 2) a continuous-flow hydrogen-fueled scramjet ground test, and 3) a segment of the HyShot II flight test. The results show that the model simulates scramjet propulsion with a reasonable degree of accuracy.
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