Shcramjet

A Shock-Induced Combustion Ramjet Engine (abbreviated as Shcramjet; also called Oblique Detonation Wave Engine (ODWE), or simply referred to as Shock-Ramjet Engine) is a concept of air-breathing ramjet engine, proposed to be used for hypersonic, as well as, single-stage-to-orbit (SSTO) propulsion applications.[1] From the overall design point of view, the shcramjet engine is similar to a scramjet engine; however, unlike the diffusive mode of combustion in scramjet engine, a shcramjet engine combustion takes place across a very thin region of standing oblique shock and/or detonation waves stabilized over a wedge, blunt body etc. Since combustion in a shcramjet engine is confined to very short region across the igniting wave, the combustor length in a shcramjet can be significantly shorter than the scramjet that requires a lengthy combustor for complete fuel-air mixing and combustion. Also, the shcramjet is believed to have a better overall propulsive performance than the scramjet at higher Mach numbers, especially above Mach 12. Recent researches have stipulated that shcramjet, alongside its other airbreathing variants such as the ramjet and scramjet, can act as an efficient high-speed vehicle propulsion system for SSTO flights.[2] These potential advantages of using the shock-induced combustion and the oblique detonation phenomena have recently attracted substantial efforts into their research for propulsive applications [3], as well as for the study of the fundamental physical phenomena. [4]

Basic Principles

The shcramjet engine geometry is extremely simple and closely similar to scramjet, the only major difference being the combustor design. The engine includes a supersonic inlet followed by a combustion chamber and a nozzle, respectively. The design principle for a shcramjet inlet is similar to a scramjet, in which the whole nose structure of waverider vehicle is used as inlet. Combustion in a shcramjet can occur in two different modes, shock-induced combustion or detonation combustion, depending on the strength of inducing shock at any Mach number. If ignition occurs far enough downstream that the ensuing combustion process does not influence the preceding shock, the combustion is said to be shock-induced. However, for extremely fast reactions, ignition occurs close to the preceding shock wave and the combustion process couples with the shock wave and forms a detonation wave.[5] Therefore, detonation wave ramjet, or oblique detonation wave engine, is only a particular case of shcramjet.

Though shock and detonation waves are related to high total pressure loss during combustion, the theoretical total pressure loss associated with shcramjet combustor approaches that of the scramjet engine at increasing Mach numbers. This fact, together with simpler engine geometry with concomitant increase in component efficiencies, results in possible superior predicted performance of the shcramjet compared to scramjet at flight Mach numbers beyond 12.

References

  1. ↑ "High Speed Vehicle Propulsion System Group". J. P. Sislian. Archived from the original on March 21, 2012.
  2. ↑ Alexander, D. C.; Sislian, J. P.; Parent, B. (2006). "Hypervelocity Fuel/Air Mixing in Mixed-compression Inlets of Shcramjets". AIAA Journal. 44 (10): 2145–55. Bibcode:2006AIAAJ..44.2145A. doi:10.2514/1.12630. Archived from the original on 2011-07-24.
  3. ↑ Bhattrai, S.; Hao, T. (2016). "Formation of near-Chapman–Jouguet oblique detonation wave over a dual-angle ramp". Aerospace Science and Technology. 63: 1–8. doi:10.1016/j.ast.2016.12.010.
  4. ↑ "Combustion and Energy Systems Research Group".
  5. ↑ Pratt, D. T.; Humphrey, J. W.; Glenn, D. E. (1991). "Morphology of Standing Oblique Detonation Waves". Journal of Propulsion and Power. 7 (5): 837–45. Bibcode:1991JPP.....7..837P. doi:10.2514/3.23399. ISSN 0748-4658. AIAA Paper 87-1785.
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