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Structural Analysis and Fabrication of a Scramjet Combustor for Future Space Transportation Systems

The scramjet is composed of three basic components: a converging inlet, where incoming air is compressed and decelerated a combustor, where gaseous fuel is burned with atmospheric oxygen to produce heat; and a diverging nozzle, where the heated air is accelerated to produce thrust. This paper explains and demonstrates the deformations and stresses developed in the scramjet combustor due to the simultaneous loading of thermal, pressure and centrifugal forces. Also, the fabrication of the combustor walls as per the design requirements is performed based on a well defined process plan with a focus on Inconel 718 super alloy machining complexities and the corresponding CNC part programs are generated using HYPERMILL cam software once the design safety is ensured.