CFD Analysis of a Hydrogen Fueled Mixture in Scramjet Combustor with a Strut Injector by Using Fluent Software

Pandey, Krishna Murari; Sivasakthivel, T.

doi:10.7763/ijet.2011.v3.208

Cited by 13 publications

(4 citation statements)

References 8 publications

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“…K.M.Pandey and T.Sivasakthivel [16] worked on the topic of "CFD Analysis of a Hydrogen Fueled Mixture in Scramjet Combustor with a Strut Injector by Using Fluent Software" they investigated supersonic cold flow with hydrogen injection. K.M.Pandey and Sivasakthivel.T [17] worked on the topic of "Recent Advances in Scramjet Fuel Injection -A Review", and their findings are -Fuel injection techniques into scramjet engines are a field that is still developing today.…”

Section: Literature Reviewmentioning

confidence: 99%

CFD Analysis of Mixing and Combustion of a Hydrogen Fueled Scramjet Combustor with a Strut Injector by Using Fluent Software

Pandey¹,

Sivasakthivel²

2011

IJET

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A numerical study of combustion enhancement has been performed for a Mach 2 model scramjet (supersonic combustion ramjet) combustor. The configuration used is similar to the DLR (German Aerospace Center) scramjet model and it is consists of a one-sided divergent channel with a wedge-shaped flame holder. Fuel (hydrogen) is injected at supersonic speed through the rear of a circular strut injector located at the channel symmetry axis. The shape of the strut is chosen in a way to produce strong stream wise vorticity and thus to enhance the hydrogen/air mixing. Strength and size of the vortices are defined by the strut geometry and may be modified. Numerically predicted profiles of static pressure, axial velocity, and static temperature for both non-reacting as well as reacting flows are compared with the experimental data. The RANS calculations are able to predict the mean and fluctuating quantities reasonably well in most regions of the flow field. Subsonic regions at the channel symmetry axis are responsible for flame holding. If the combustor geometry is chosen in a favorable way these subsonic zones may be kept small. The k-ε computations are capable of predicting mixing and combustion simulations well and good.

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Section: Literature Reviewmentioning

confidence: 99%

CFD Analysis of Mixing and Combustion of a Hydrogen Fueled Scramjet Combustor with a Strut Injector by Using Fluent Software

Pandey¹,

Sivasakthivel²

2011

IJET

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“…The flow field within the combustor of the scramjet engine is very complex and has a tremendous impact on the optimum supersonic combustor design. Sufficient mixing to the extent that the desired combustion reaction and heat release can occur requires a detailed understanding of fuel injection and fluid interaction processes [4].…”

Section: Introductionmentioning

confidence: 99%

Numerical simulations of single and multi-staged injection of H2 in a supersonic scramjet combustor

Abu‐Farah¹,

Haidn²,

Kau³

2014

Propulsion and Power Research

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Computational fluid dynamics (CFD) simulations of a single staged injection of H 2 through a central wedge shaped strut and a multi-staged injection through wall injectors are carried out by using Ansys CFX-12 code. Unstructured tetrahedral grids for narrow channel and quarter geometries of the combustor are generated by using ICEM CFD. Steady three-dimensional (3D) Reynolds-averaged Navier-stokes (RANS) simulations are carried out in the case of no H 2 injection and compared with the simulations of single staged pilot and/or main H 2 injections and multistage injection. Shear stress transport (SST) based on k-ω turbulent model is adopted. Flow field visualization (complex shock waves interactions) and static pressure distribution along the wall of the combustor are predicted and compared with the experimental schlieren images and measured wall static pressures for validation. A good agreement is found between the CFD predicted results and the measured data. The narrow and quarter geometries of the combustor give similar results with very small differences. Multi-staged injections of H 2 enhance the turbulent H 2 /air mixing by forming vortices and additional shock waves (bow shocks).

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“…This results in a forward velocity. Ramjets work most efficiently at supersonic speeds around Mach 3 (2,284 mph; 3,675 km/h) [1][2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Modelling and Exhaust Nozzle Flow Simulations in a Scramjet

Ks¹,

Dk²

2015

J Astrophys Aerospace Technol

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This project will be aimed at modelling the supersonic flow inside Scramjet engine using the Computational Fluid Dynamics CFD ANSYS Fluent. Scramjet Engine starts at a hypersonic free stream Mach no. 5.00. When pressures and temperatures become so high in supersonic flight that it is no longer efficient to slow the oncoming flow to subsonic speeds for combustion, a scramjet (supersonic combustion ramjet) is used in place of a ramjet. Supersonic flow from a nozzle that represents the exhaust nozzle of a supersonic combustion ramjet SCRAMJET is modelled. Jet from the nozzle is issued into a domain which is bounded on one side by an after body wall which is parallel to the center line of the nozzle. Shocks propagating from the nozzle exit reflect from the after body. Outflow from scramjet engines can have a significant impact on both the heat transfer and the pressure distribution on the section of the aircraft that lies downstream. Most importantly, reflecting shock waves lead to large peaks in the distributions. Two geometrical configurations for the after body are tested. Experimental values are used because this span wise region is closest to the centre of the experimental model where the three-dimensional effects are minimal. Measured values of the distribution of wall pressure and heat transfer rate along the after body are used to validate the CFD simulation.

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CFD Analysis of a Hydrogen Fueled Mixture in Scramjet Combustor with a Strut Injector by Using Fluent Software

Cited by 13 publications

References 8 publications

CFD Analysis of Mixing and Combustion of a Hydrogen Fueled Scramjet Combustor with a Strut Injector by Using Fluent Software

CFD Analysis of Mixing and Combustion of a Hydrogen Fueled Scramjet Combustor with a Strut Injector by Using Fluent Software

Numerical simulations of single and multi-staged injection of H2 in a supersonic scramjet combustor

Modelling and Exhaust Nozzle Flow Simulations in a Scramjet

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