Title
Swirl-Stabilised Hydrogen Combustor with Axial Air Injection: Numerical Simulations and Cold Flow Experiments
Author
Vermeijlen, Simon (TU Delft Aerospace Engineering)
Contributor
Gangoli Rao, A. (mentor) 
Degree granting institution
Delft University of Technology
Programme
Aerospace Engineering
Project
Advanced Propulsion and Power Unit (APPU)
Date
2021-07-02
Abstract
Swirl-stabilised hydrogen combustion has great potential in the aviation industry since emissions can be significantly reduced compared to fossil fuels. However, a major drawback is a high proneness to flashback. This could be overcome with non-swirling axial air injection (AAI) on the centre-line of the mixing tube. The effect of this concept on the effective Swirl number and flashback propensity was investigated for a radial- and axial swirl generator by Computational Fluid Dynamics (CFD) simulations and cold flow Particle Image Velocimetry (PIV) experiments on a custom-designed combustor model. Acquired results indicate that with increasing amount of AAI the Swirl number reduces due to both inertial and viscous effects. The flashback propensity also reduces as the axial velocity on the centre-line increases by AAI. For equal Swirl numbers the axial swirl generator was found to have a lower flashback propensity compared to the radial swirl generator, suggesting safer operation.
Subject
Swirling flow
Combustor
Lean premixed hydrogen combustion
PIV
CFD
Vortex breakdown
Axial swirl generator
Radial swirl generator
To reference this document use:
http://resolver.tudelft.nl/uuid:bb2c1c3d-f4bc-47e4-b694-34d493f628b2
Embargo date
2024-07-02
Coordinates
51.988610, 4.376159
Part of collection
Student theses
Document type
master thesis
Rights
© 2021 Simon Vermeijlen