Numerical study of the interaction between a sonic transverse jet with an oblique shock wave in a supersonic crossflow

Master thesis (2023)

Authors

G. Sofia-Gabrion Aerospace Engineering

Contributors

F.F.J. Schrijer Aerodynamics - Aerospace Engineering (supervisor 1)
B.W. van Oudheusden Aerodynamics - Aerospace Engineering (supervisor 2)
S.J. Hulshoff Aerodynamics - Aerospace Engineering (supervisor 2)
Faculty
Aerospace Engineering
Copyright: © 2023 Grégoire Sofia-Gabrion
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Published Date

23-10-2023

Language

English

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Faculty

Aerospace Engineering

Abstract

A series of numerical simulations was executed using the high-performance cluster at TU Delft's Aerospace Faculty. The primary objective was to gain deeper insights into the intricate dynamics of a sonic transverse jet in a supersonic crossflow with an oblique induced shock wave, especially concerning mixing. These simulations delved into the near and mid-field regions, illuminating how the position and intensity of an induced oblique shock wave affect the original jet in crossflow configuration.

In a simplified context, a box simulated the combustion chamber near the injector. A transverse jet was introduced through a lower wall hole, intersecting the incoming crossflow. Wedges on the upper wall generated induced shocks at varying distances from the jet exit. These experiments spanned different locations and strengths of shock impingements, all relative to the diameter of the jet's injection port hole.

The investigation aimed to comprehend how an additional shock wave influences mixing within the combustor. In the upstream scenario, the shock's proximity to the jet exit led to enhanced compression and the emergence of Kelvin-Helmholtz instability. Downstream impingement, on the other hand, disrupted the usual behavior of this instability. In both cases, the initial downward movement of fluid structures toward the wall was followed by ascent, expanding the region for crossflow-wall mixing downstream. Close-to-jet exit shock impacts intensified these effects, causing explosive disruptions and enhanced mixing.

Ultimately, the study revealed that closer and more intense shock impacts near the jet exit had a significant negative impact on volumetric energy, detrimental to combustion and propulsion potential. Optimal results were achieved when the shock impingement occurred farther downstream. The research also highlighted the need for improvements in simulation techniques and recommended further exploration of various parameters for comprehensive insights. This work serves as a foundation for future studies tailored to specific needs, promising more insightful outcomes.