ADVANCES IN MIXING AND COMBUSTION MODELLING IN SUPERSONIC FLOWS

Paper number

IAC-24,C4,7,2,x91447

Author

Mr. Sasi Kiran Palateerdham, University of Rome “La Sapienza”, Italy

Coauthor

Mr. Lakshmi Narayana Phaneendra Peri, Scuola di Ingegneria Aerospaziale "La Sapienza", Italy

Coauthor

Dr. Antonella Ingenito, Sapienza University of Rome, Italy

Coauthor

Prof. Choubey Gautam, National Institute of Technology Silchar, India

Year

2024

Abstract

Understanding mixing in compressible flows is pivotal in advancing scramjet technology for future aerospace applications. Explorations into improving mixing encompass different techniques, including vortex generators, cavities, and the crossflow injection. These strategies exhibit potential in augmenting mixing efficiency, but concurrently, they introduce a challenge: heightened total pressure.

Inadequate mixing results in incomplete combustion, ultimately diminishing both engine efficiency and thrust, efficient mixing often comes at the expense of elevated total pressure losses. The challenge of balancing efficient mixing and pressure losses in scramjet technology is a critical issue, still open. In this context, advanced simulations, experimental testing, and optimization techniques are fundamental to address this challenge. In fact, achieving the right balance is a key to realizing the full potential of scramjets for future hypersonic flights, where both high efficiency and high thrust are required.

In this context, the research aim to analyse the characteristics of turbulence in compressible flow, by means of a theoretical analysis and to validate this analysis by means of large eddies numerical simulations of the HIFiRE test case. research work provides an investigation of the effect of shocks development and interaction with the mainstream by means of LES. The flow field within the HIFiRE-2 combustor has been analysed at different conditions. Combustion models have used implemented to account for the kinetic times.  LES simulations of the HIFiRE-2 scramjet showed the direct and mutual effects of the shock waves interaction with the vorticity, the heat addition, friction, mixing, boundary layer separation on the total pressure losses.

Abstract document

IAC-24,C4,7,2,x91447.brief.pdf

Manuscript document

IAC-24,C4,7,2,x91447.pdf (🔒 authorized access only).

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