Numerical Analysis of Hypersonic Combustion without Cavity Based Injection with Finite Rate Chemistry Model
نویسنده
چکیده
In this part of the investigation, flow-field properties of hydrogen jets injected into a hypersonic flow are reported. The combustor has a single fuel injection parallel to the main flow from the base. The numerical simulation has been done with finite rate chemistry model using K-ε turbulence model. The results obtained through the numerical simulation of the cavity based fuel injectors are presented. The main issue in supersonic combustion is proper mixing within short burst of time. The result shows the better mixing of fuel and the flame speed increases almost linearly. The stagnation temperature in the combustion reaches up to 2510 k.
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