Effect of location of a transverse sonic jet on shock augmented mixing in a SCRAMJET engine

Sharma, Vatsalya; Eswaran, V.; Chakraborty, Debasis

doi:10.1016/j.ast.2019.105535

Cited by 24 publications

(3 citation statements)

References 29 publications

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“…A large-eddy simulation of transverse jet injection into a supersonic flow was performed in [29]. The effects of different injection schemes on a transverse jet in a supersonic crossflow were discussed in [30][31][32]. The implementation of the required value of the control force at the minimum flow rate of the injected gas was carried out when the injection hole was located at a distance of 0.3-0.4 of the length of the main nozzle from its outlet and the injection angle was 110-130 • towards the nozzle axis towards the flow [33,34].…”

Section: Introductionmentioning

confidence: 99%

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

2021

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The optimal design of the thrust vector control system of solid rocket motors (SRMs) is discussed. The injection of a supersonic underexpanded gas jet into the diverging part of the rocket engine nozzle is considered, and multiparameter optimization of the geometric shape of the injection nozzle and the parameters of jet injection into a supersonic flow is developed. The turbulent flow of viscous compressible gas in the main nozzle and injection system is simulated with the Reynolds-averaged Navier–Stokes (RANS) equations and shear stress transport (SST) turbulence model. An optimization procedure with the automatic generation of a block-structured mesh and conjugate gradient method is applied to find the optimal parameters of the problem of interest. Optimization parameters include the pressure ratio of the injected jet, the angle of inclination of the injection nozzle to the axis of the main nozzle, the distance of the injection nozzle from the throat of the main nozzle and the shape of the outlet section of the injection nozzle. The location of injection nozzle varies from 0.1 to 0.9 with respect to the length of the supersonic part of the nozzle; the angle of injection varies from 30 to 160 degrees; and the shape of the outlet section of the injection nozzle is an ellipse with an aspect ratio that varies from 0.1 to 1. The computed fluid flow in the combustion chamber is compared with experimental and computational results. The dependence of the thrust as a function of the injection parameters is obtained, and conclusions are made about the effects of the input parameters of the problem on the thrust coefficient.

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Section: Introductionmentioning

confidence: 99%

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

2021

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“…Also recent studies from Huh and Lee [21], Zhao et al [22], Williams et al [30], Liu et al [24] numerically investigated the interaction of the jets with supersonic cross flow using high fidelity numerical methods. In addition various authors examined jets in supersonic cross flow in a scramjet engine, numerically [27], [28], [29], [30]. Specifically Miller et al [25] numerically investigated transient interaction between a reaction control jet and Mach 5 cross flow using data from the thesis of Erdem [26].…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of sonic transverse jets in Mach 5 crossflow

Erdem

Kontis

2021

Aerospace Science and Technology

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“…Sharma et al [20] used Menter's shear-stress transport (SST) model in the computational fluid dynamics (CFD) solver to perform the 3-D Reynolds Average Navier-Stoke (RANS) method on configurations in which jets were placed at various locations downstream of the step. The author indicated that mixing is strongly affected by the distance between the steps and the jet.…”

Section: Introductionmentioning

confidence: 99%

Effect of the Backward Facing Step on a Transverse Jet in Supersonic Crossflow

Zhang¹,

Wang²,

Sun³

et al. 2020

Energies

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A transverse jet in the supersonic crossflow is one of the most promising injection schemes in scramjet, where the control or enhancement of jet mixing is a critical issue. In this paper, the effect of the backward facing step on the characteristics of jet mixing was investigated by three-dimensional large eddy simulation (LES). The simulation in the flat plate configuration (step height of 0) was performed as the baseline case to verify the computation framework. The distribution of the velocity and pressure obtained by the LES agreed well with the experiment, which shows the reliability of the LES code. Then, two steps with a height of 1.0D and 1.58D (D is the injector diameter) were numerically compared to the non-step baseline case. The comparison of the three cases illustrates the effect of the large-scale recirculation region on the variable distribution, and shock and vortex structures in the flow field. In the windward region, the shear layers become thicker, and the convection velocity of the shear vortexes reduces. In the leeward region, the wake vortices almost disappear while the counterrotating vortex pairs (CVPs) expand in the spanwise direction. In the area upstream of the jet, the separation bubble works with the upstream large-scale recirculation zone to entrain the jet into the upstream near-wall zone. At last, a comparison of the overall mixing performance of the three cases revealed that the penetration depth and mixing efficiency increased with the step height increasing.

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Effect of location of a transverse sonic jet on shock augmented mixing in a SCRAMJET engine

Cited by 24 publications

References 29 publications

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle

Experimental investigation of sonic transverse jets in Mach 5 crossflow

Effect of the Backward Facing Step on a Transverse Jet in Supersonic Crossflow

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