Effect of different strut + wall injection techniques on the performance of two-strut scramjet combustor

Choubey, Gautam; Pandey, Krishna Murari

doi:10.1016/j.ijhydene.2017.04.024

Cited by 112 publications

(15 citation statements)

References 54 publications

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“…The combustion of hydrogen-air mixture starts in the form of exothermic reaction, and its heat energy generates detonation wave. Therefore, simulation is initiated with single-step reduced chemical kinetics with finite-rate/eddy-dissipation method [37][38][39]. The outer cylindrical surface wall and left wall of PDE tube are considered to be an adiabatic (i.e., heat transfer throughout the system or into the system is zero) with the no-slip condition [40,41], whereas the boundary of right-side open end tube is considered as pressure outlet.…”

Section: Initial and Boundary Conditionmentioning

confidence: 99%

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Alam

Sharma

Pandey

2019

J Braz. Soc. Mech. Sci. Eng.

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Pulse detonation engine is a new technique of supersonic wave propagation and stands for high impulsive thrust. The objective of the present investigation is to analyze the detonation wave characteristic of a hydrogen-air mixture in the pulse detonation engine (PDE) having obstacles of blockage ratio 0.5. The three-dimensional reactive Navier-Stokes equations with realizable k − ɛ turbulence model are used to simulate the propagation of combustion flame. The reaction rate of excess hydrogen and excess air is modeled by reduced single-step chemical reaction model and simulated using ANSYS software FLUENT 14.0 code. The simulation results of the shock wave overpressure, deflagration-to-detonation transition run-up distance of different flames and flame velocities are reported at initial boundary condition of 0.1 MPa pressure and 293 K temperature. It has been observed that the obstacles create turbulence in the propagating flame and form strong Mach stems of high temperature, resulting in reduction in accelerated flame run-up length. However, the normalized detonation flame run-up distance increases as the mass of fuel increases in the mixture. Thus, the performance of PDE combustor was observed 4.46% at high overpressure generated by excess fuel (ϕ = 1.3).

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Section: Initial and Boundary Conditionmentioning

confidence: 99%

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Alam

Sharma

Pandey

2019

J Braz. Soc. Mech. Sci. Eng.

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“…[13][14][15][16] Meanwhile, several books and papers have been published in this field of study. [17][18][19][20][21][22] The film injection, cavity technique, and porthole injections are the most conventional approaches for the fuel injection system. Some of the scholars concentrated on the application of the strut as a shock producer or free stream deflector for mixing augmentation of the fuel jets.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, computational fluid dynamics as a virtual laboratory is extensively used for research in this field. [35][36][37][38][39][40] The key advantage of the computational approach is low cost and informative results about details of flow feature. [41][42][43][44][45] Thus, several codes and software are developed for the simulation of compressible flow inside the scramjet engine.…”

Section: Introductionmentioning

confidence: 99%

Computational investigation of multi hydrogen jets at inclined supersonic flow

2020

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Summary Scramjet design is directly associated with the fuel mixing inside the combustor. In this study, the influences of the free stream angle on the fuel mixing zone of eight microjets are fully investigated. This study mainly tries to disclose the importance of the fuel jet interaction with a supersonic free stream on penetration and distribution of hydrogen jets. The effects of jet paces and different free stream angles are fully examined in this work. For the computational study, CFD numerical method is applied to obtain the fuel jet structure at supersonic cross‐flow. RANS equations with SST turbulence scheme is employed for the simulation of our model. Our simulations show that a positive angle of supersonic incoming flow is effective for the uniform expansion of the fuel mixing zone inside the combustor. According to our findings, increasing the angles of the free stream declines the mixing zone when the fuel jet interaction of the last jets with main stream decreases. Our results indicate that mixing efficiency of ‐20° is about 30% more than other angles.

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“…A comprehensive study of different strut configurations and fuel injection locations has been conducted. [20][21][22][23][24] It was observed that in order to reduce the pressure loss in the combustion and enhance efficiency, it was necessary to augment and accelerate the mixing between the air and the fuel. Two half-angled strut configuration was tested and with different attack angles and found that configuration at zero attack angle had better combustion and maximum peak temperature in comparison to configuration with attack angle -3 and 3 , and a single strut.…”

Section: Introductionmentioning

confidence: 99%

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

et al. 2020

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Supersonic combustion ramjet (scramjet) is a variant of ramjet in which the combustion takes place at supersonic velocity. The flow physics inside the scramjet combustor is quite complex due to the fact that the mixing and completion of the combustion take place in a short time, which is of the order of milliseconds. This study focuses on flow characteristics within the combustion chamber of the scramjet engine that is designed to improve energy efficiency by enhancing combustion efficiency. The effect on combustion performance and thereby the energy efficiency on using strut-based flame stabilizer is evaluated at different positions. Reynolds averaged Navier-Stokes equations are solved with the Shear Stress Transport k-ω turbulence model. Single strut configuration is used to validate with the experimental data. Single strut is then compared with three-strut configuration. In the three-strut configuration, the location of the primary strut is kept constant, and the secondary struts are relocated in x and y directions. Combustion performance was evaluated for the cases of flow from primary strut only and through three struts. It was found that the placement of secondary strut in a three-strut configuration plays a vital role in improving energy efficiency. A maximum of 33.86% improvement in combustion efficiency was observed in comparison to the single strut combustor. A reduction in unburned fuel was observed, making the system more energy efficient. If the struts are not placed optimally, the combustion performance of the combustor was observed to be lower than that of a single-strut configuration. The shock reflection and expansion fans within the primary combustion zone and the secondary strut region enhance the combustion efficiency. The wall static pressure was observed to increase with the addition of secondary struts. For certain strut configurations, flow separation was seen on the combustor walls. If the secondary strut was placed close to the primary strut, combustion efficiency was found to enhance. It was seen that

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Effect of different strut + wall injection techniques on the performance of two-strut scramjet combustor

Cited by 112 publications

References 54 publications

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Computational investigation of multi hydrogen jets at inclined supersonic flow

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

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