Effect of variation of length-to-depth ratio and Mach number on the performance of a typical double cavity scramjet combustor

Mahto, Navin Kumar; Choubey, Gautam; Suneetha, Lakka; Pandey, Krishna Murari

doi:10.1016/j.actaastro.2016.08.010

Cited by 97 publications

(3 citation statements)

References 40 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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.

View full text Add to dashboard Cite

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).

show abstract

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.

View full text Add to dashboard Cite

show abstract

“…38 Even if CFD represents the flow effectively at high Reynolds numbers and accurately calculates the large-scale phase separation, it is time consuming and costly, reducing the availability for airflow layout analysis. Instead, a detailed k-omega model 39 can be utilized to examine the impacts of multiple changes in the intake and geometric conditions.…”

Section: Introductionmentioning

confidence: 99%

A computational study of leading-edge wall cooling effect on shock wave–boundary layer interaction in forward-facing step

Murugan

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

A computational study has been done to understand the effect of leading-edge wall cooling on shock wave–boundary layer interaction. Shock wave–boundary layer interaction is studied over a forward-facing step at supersonic Mach 2.5. The study was carried out using Ansys. The work aims to explore the implementation of wall cooling at the leading edge as a separation control strategy for supersonic forward-facing step-induced flow separation. We use a finite-volume method based on upwind flux difference splitting and second-order upwind flow discretization. The simulation results are validated with the available experimental data. Furthermore, using numerical simulations, we found that the separation bubble size was reduced by 18.36% when the walls were marginally cooled to 150 K, while the separation was reduced by 32.65% when the walls were strongly cooled to 100 K.

show abstract

“…To simulate the combustion in reflected muzzle flow, a numerical model based on the Navier‐Stokes equations and

k - ϵ

turbulence model is established. The

k - ϵ

turbulence model has been validated with experimental data for combustion in supersonic flows . A solid propellant combustion model is coupled with the model.…”

Section: Introductionmentioning

confidence: 99%

Study on the Initiation Mechanism of Non‐Premixed Shock Induced Combustion in Supersonic Propellant Gas Jet

Qin

Zhang

2019

Propellants Explo Pyrotec

View full text Add to dashboard Cite

The reflection of a supersonic propellant gas jet always happens during the firing of the weapon system of aircraft. The reflection induces complex non‐premixed shock induced combustion. It is of great importance to investigate the initiation mechanism of the combustion in the supersonic jet of propellant gas. The mechanism is vital for the design of any suppression method of the secondary combustion. To investigate the combustion in the reflected supersonic jet, a solid propellant combustion model and a numerical model based on compressible multispecies Navier‐Stokes equations are established. A detailed reaction mechanism consisting of 9 species and 12 reactions is utilized for the combustion of the propellant gas. Based on the models, the supersonic precursor flow field and the supersonic propellant gas jet flow are obtained and discussed. A secondary jet is observed which has not been reported before. A sandwich structure is proposed to reveal the initiation of the combustion. The oxygen supply in the secondary jet is found to be dominated by a vortex. An inert gas atmosphere can be adopted to suppress the mass transfer at the contact surface. Special devices could be designed to suppress the formation of the vortex in the secondary propellant jet.

show abstract

Effect of variation of length-to-depth ratio and Mach number on the performance of a typical double cavity scramjet combustor

Cited by 97 publications

References 40 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

A computational study of leading-edge wall cooling effect on shock wave–boundary layer interaction in forward-facing step

Study on the Initiation Mechanism of Non‐Premixed Shock Induced Combustion in Supersonic Propellant Gas Jet

Contact Info

Product

Resources

About