An Aerothermodynamic Design Approach for Scramjet Combustors and Comparative Performance of Low-Efficiency Systems

Abstract:

This paper is aimed at development of an integrated approach based on analytical and computational aerothermodynamics for the special case of design of a 75% (low process-efficiency), hydrogen-fuelled, constant area combustor of a hypersonic airbreathing propulsion (HAP) system thereafter undertaking study of two types of HAP systems. The results of configurational aerothermodynamics implied that the most appropriate constant area configuration had a 30 degrees downstream wall-mounted fuel injector with a single acoustically stable cavity placed downstream of the fuel injection point. Moreover for identical flow inlet parameters and system configurations at lower levels of thermodynamic process efficiencies, the constant combustor-area (i.e. Scramjet 1) engine is superior in its performance to the constant combustor-pressure (i.e. Scramjet 2) engine for all values of fuel-air ratios.

• Periodical: Applied Mechanics and Materials (Volumes 110-116)
• Pages: 4652-4660
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.110-116.4652
• Online since: October 2011
• Authors: Ali Sarosh, Dong Yun Feng, Muhammad Adnan
• Keywords: Acoustic Cavities, Configurational Aerothermodynamics, Hypersonic Airbreathing Propulsion (HAP), Shear Layer Method, Stream Thrust Method

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