Numerical Investigation on Hydrogen-Fueled Scramjet Combustor with Parallel Strut Fuel Injector at a Flight Mach Number of ۶

A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = ۶ with parallel injection (Strut with circular inlet) is presented in the present research article. Three different angles of attack (α=-۴°, α=۰°, α=۴°) have been studied for parallel injection. The scramjet configuration used here is a modified version of DLR scramjet model. Fuel is injected at supersonic speed (M=۲) through a parallel strut injector. For parallel injection, the shape of the strut is chosen in a way to produce strong stream wise vorticity and thus to enhance the hydrogen/air mixing inside the combustor. These numerical simulations are aimed to study the flow structure, supersonic mixing, and combustion phenomena for the three different types of geometries along with circular shaped strut configuration.

کلیدواژه ها:

Scramjet ، Hypersonic Combustion ، k−ε Realizable model ، Parallel injector