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Reduced kinetics model for hydrogen/air combustion in supersonic flows

Reduced kinetics model for hydrogen/air combustion in supersonic flows
Typ:Bachelor- o. Masterarbeit
Datum:nach Absprache
Betreuer:

Yekaterina Moisseyeva

Links:Text als PDF

Supersonic propulsion is a prospective technology for transport systems, using which it can be possible to reach superfast speeds (>5000 km/h) with an aircraft. It is high efficiency and clean technology since it is based on the hydrogen fuel.

Complex process in a supersonic ramjet (scramjet) involves interaction of gas dynamics and combustion and includes shock waves, vortices, turbulence, compressibility, and other effects. Development based solely on tests is too slow and expensive, so the use of numerical simulations becomes the main tool to aid development of supersonic ramjet.

In the simulated scramjet engine, hydrogen is injected into a supersonic air cross-flow (Mach number M = 4). Flow, mixing and chemical reaction are simulated using a CFD Code based on the Favre-averaged Navier-Stokes equations.

Detailed mechanisms of reaction consist of a large number of chemical species and a large number of elementary reactions, so treatment of detailed chemical reaction becomes computationally expensive. There is a strong need for development of an advanced reduced modelling concept, and the REDIM method can be used for simplified (yet realistic) treatment of reaction.

The considered mathematical models include a variety of physicochemical processes taking place in areas of complex configuration, and therefore the developed techniques are applicable to the analysis of a wide class of supersonic flows of a homogeneous viscous gas and chemically reacting gas mixtures with heat transfer.