Abstract
Through Computational Fluid Dynamics and validation, an optimal scramjet combustor has been designed based on twin-strut Hydrogen injection to sustain flight at a desired speed of Mach 8. An investigation undertaken into the efficacy of supersonic combustion through various means of injection saw promising results for Hydrogen-based systems, whereby strut-style injectors were selected over transverse injectors based on their pressure recovery performance and combustive efficiency. The final configuration of twin-strut injectors provided robust combustion and a stable region of net thrust (1873 kN) in the nozzle. Using fixed combustor inlet parameters and injection equivalence ratio, the finalized injection method advanced to the early stages of two-dimensional (2-D) and three-dimensional (3-D) scramjet engine integration. The overall investigation provided a feasible supersonic combustion system, such that Mach 8 sustained cruise could be achieved by the aircraft concept in a computational design domain.
Highlights
Commercial air travel is an ever-expanding industry seeing strong year-on-year growth withInternational Air Transport Association’s (IATA) 2035 forecast estimating a doubling of the 7.2 billion passengers measured in 2016
Since the pressure of the staggered injectors is reduced by a factor of thirds compared to the aligned arrangement, the bow shock induced by the initial interaction is two thirds compared the aligned arrangement, the bow shock induced by the initial interaction
The net performance of the twin strut arrangement is very similar to Case 4, where the average total pressure recovery in the side flow regions is maintained at 96%, while an fuel injector velocity
Summary
Commercial air travel is an ever-expanding industry seeing strong year-on-year growth with. Hypersonic transport has potential to be the general mode of air transport, with speeds of over Mach 5 Such a concept could traverse the Heathrow to JFK route in half of Concorde’s 4-h flight time, but would be faced with demanding engineering challenges in order to meet strict regulatory laws. With any engineering challenge of this sensitivity and complexity, there are a multitude of challenges associated with sustained hypersonic flight and achieving robust combustion in fairly severeoperating operating conditions. 8, at which conditions necessitate the usage of a scramjet engine, the requirements of which which are to provide robust sustained combustion. Such sustained operation would facilitate the are to provide robust sustained combustion.
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