Abstract
In ramjet and scramjet engines, fuel–air mixing flame and combustion stability are critical in determining the thermodynamic performances of such supersonic propulsion systems. In this chapter, the combustion instability of a solid-fueled ramjet is investigated first using a 2D numerical model. Effects of inlet thermodynamic properties, such as inlet temperature and mass flow rate are evaluated. Attempts are then made to enhance flame stabilization in a Ramjet trapped vortex combustor (cavity-holder) with a guide vane implemented. Systematic firing tests are then experimentally conducted on a solid-fueled Ramjet engine with paraffin-polyethylene blends fueled to examine the engine’s thermodynamic performances and combustion behaviors. In general, this chapter overviews the recent investigations on the combustion and flame stability and fuel–air mixing characteristics in modeled Ramjet and lab-scale Ramjet test rig.
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