A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = 6 with parallel injection (Strut with circular inlet) is presented in the present research article. Three different angles of attack (α=-4°, α=0°, α=4°) 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=2) 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.
Numerical analysis of the hypersonic combustion and flow structure through a scramjet engine at a flight Mach 7 with parallel fuel injection at different angles of attack, α= (-5°), 0° and 5° have been studied in the present research paper. The scramjet configuration incorporates an inlet angle of 8 o compression ramp followed by an insulator and a divergent combustor for parallel injection. The shape of the strut is chosen such that it produces strong stream wise vorticity and thus enhances the air/fuel mixing. These numerical simulations were aimed to study the flow structure, supersonic mixing and combustion efficiency. For parallel injection investigation; the influence of strut injector, the variation of angle of attack on the flow behavior in reacting cases have been studied. The shock structure and combustion phenomenon are affected by the combustor geometry, flight Mach number and by the trajectory.
The present work address the CFD analysis for scramjet combustor with diamond-shaped strut injectors at supersonic Mach 4.5 and it’s based on species transport combustor which is standard k-epsilon turbulence model. It is implied for supersonic combustion that the ramjet engine is focused for operating high speed engines. The combustion chamber assists as an envelope to clutch the propellant for a satisfactory period to certify complete mixing as well as combustion. The diamond-shaped strut injector gives the maximum temperature and pressure of 3517 K and 1.487 MPa respectively whereas the combustion efficiency is found to be 87.2%. The shear layers losses are extremely minimize the performance of the engine, thus interpreting trade-off programmes in a very difficult way to achieve maximum combustion efficiency. Further firmness by machines is essential for achieving higher combustion efficiency.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.