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Numerical analysis of detonation combustion wave in pulse detonation combustor with modified ejector with gaseous and liquid fuel mixture

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Abstract

The detonation combustion phenomenon is supersonic combustion process and follows on thermal explosion in combustor. Deflagration to detonation transition occurs in detonation tube due to pressure oscillation in PDE combustor, which is driven by acoustic combustion phenomena in detonation tube. As this combustion process has great significance role for future propulsion system, the present objective is to investigate the effect of modify ejector having half angles of α = (− 4°, 0°, + 4°) on detonation combustion wave propagation regime. Further the propulsion thrust of liquid kerosene and gaseous hydrogen–air mixture are also analyzed. This numerical simulation has been analyzed by LES turbulence model for DDT and shock wave pressure oscillation in pulse detonation combustor at Fluent based CFD plat form. The one-step irreversible chemical kinetics model analyzes the details exothermic chemical reaction mechanism inside the combustor. However, the shrouded ejector with taper angle of α = +4° performed the strong starting vortex generation and shortest possible time of 0.032 s for fully developed detonation wave. The simulation results also shows that thrust force augmentation of hydrogen–air mixture is greater compared to combustion process of liquid kerosene–air mixture with significant magnitude of 38 N. Although kerosene–air mixture produces less pollutant number but the propagation flame velocity is 2550 m s−1 for hydrogen/air mixture, which is near about C–J velocity and comparatively higher than kerosene/air combustion process.

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Abbreviations

Ma:

Mach number

d :

Diameter

D th :

Throat diameter

L :

Length

t :

Time

s :

Second

ρ :

Density

µ :

Kinematic viscosity

p :

Pressure

T:

Temperature

h :

Enthalpy

e :

Internal energy

m :

Mole concentration

ϕ :

Equivalent ratio

α :

Taper angel

Y i :

Mass fraction

CFD:

Computational fluid dynamics

CEA:

Chemical equilibrium and applications

CJ:

Chapman Jouguet

PDE:

Pulse detonation engine

LES:

Large eddy simulation

DDT:

Deflagration to detonation transition

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Acknowledgements

The authors would like to express gratitude to the Mechanical Engineering Department, NIT Agartala, Tripura: 799046, India, for providing the computer facilities.

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Authors and Affiliations

  1. Mechanical Engineering Department, National Institute of Technology Agartala, Agartala, Tripura, 799046, India

    Pinku Debnath

  2. Mechanical Engineering Department, National Institute of Technology Silchar, Silchar, Assam, 788010, India

    K. M. Pandey

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  1. Pinku Debnath
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  2. K. M. Pandey
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Correspondence to Pinku Debnath.

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Debnath, P., Pandey, K.M. Numerical analysis of detonation combustion wave in pulse detonation combustor with modified ejector with gaseous and liquid fuel mixture. J Therm Anal Calorim 145, 3243–3254 (2021). https://doi.org/10.1007/s10973-020-09842-1

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  • DOI: https://doi.org/10.1007/s10973-020-09842-1

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