Scramjet Engine

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PERFORMANCE CHARACTERISTIC OF SUPERSONIC COMBUSTION CHAMBER 1, V.Thenambika1 1PG Student, Department of Mechanical Engineering, Bannari Amman Institute of Technology, Tamilnadu -638401 Abstract As one of the most promising propulsive systems in the future, the scramjet engine has drawn the attention of many researchers. The two-dimensional coupled implicit NS equations, the standard k-ε turbulence model and the finite-rate/eddy-dissipation reaction model have been applied to numerically simulate the flow field of the hydrogen fueled scramjet combustor with a planer strut flame holder under two different working conditions, namely, cold flow and engine ignition. The obtained results show that the numerical method used in this paper is suitable…show more content…
The shock generator is an effective method to accelerate the combustion. The increase of the injection total pressure raises the penetration of fuel;thus, the reaction zone expands to the center of flow field. Gruenig and F. Mayinger worked on the topic of “Supersonic combustion of kerosene/h2-mixtures in a model Scramjet combustor”, and their findings are – The necessary temperature level is partly achieved by the oblique shock waves in the supersonic flow with increasing combustor area.ratio. K.M.Pandey and T.Sivasakthivel 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. Kyung Moo Kim et.al worked on the topic of “Numerical study on supersonic combustion with cavity-based fuel injection”, and their findings are – When the wall angle of cavity increases, the combustion efficiency is improved, but total pressure loss…show more content…
A schematic of the DLR (German Aerospace centre) scramjet experimental facility is presented in Fig. Preheated air is expanded through a Laval nozzle and enters the combustor section at Ma = 2.0. The combustor has a width of 40 mm and a height of 50 mm at the entrance and a divergence angle of the upper channel wall of three degrees to compensate for the expansion of the boundary layer. A planer wedge shaped strut is placed in the combustion chamber downstream of the nozzle. Just downstream of the nozzle the height of the 32 mm long strut is 0.295 mm. along the first 100 mm downstream of the nozzle, the side walls and the upper wall are made from quartz glass to allow optical access and to minimize the reflection of scattered light on the wall opposite the observation window. Hydrogen (H2) is injected at Ma = 1.0 through a planer strut injector with diameter of 0.295 mm, in the strut base. Typical mass flows in the experiments were varied between 1.0 and 1.5 kg/s for the air and between 1.5 and 4.0 g/s for H2, which correspond to equivalence ratios between 0.034 and 0.136, respectively. The hydrogen is injected at ambient temperature and pressure, i.e. at T = 250 K and p =105Pa, whereas the air was injected at T = 340 K and p =105Pa Figure 1: Geometry of Chamber CATIA MODELLING OF 3D COMBUSTION CHAMBER In the computational
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