Design and analysis of an inlet and combustion chamber of scramjet engine

Abstract

Scramjet is an air-breathing engine that uses the oblique or conical shock waves generated during the hypersonic/supersonic flight, to promote compression and deceleration of free stream atmospheric air at the inlet of the scramjet. The combustion includes turbulent mixing, shock interaction and heat release in supersonic flow. The problem associated with combustion is mixing of fuel with air. The scramjet engine can be operating at Mach no. 3.4 to 5 in order to eliminate other propulsive engine. Here the number of ramps and the ramp angle is changed and the thickness and length of combustion chamber is changed. If the length and thickness of the combustion chamber is changed then the fuel will get enough time to mix with air to achieve the desirable thrust. The main objective of this project is to design a scramjet inlet and combustion chamber for efficient fuel combustion by flow analysis. This includes the variation of flow from inlet and combustion chamber by considering the boundary conditions of scramjet engine design. The flow analysis is carried out here by using computational fluid dynamics (CFD) and the modelling of engine's inlet and combustion chamber is done using CATIA.