To further advance combustion technology, this thesis analyzes a counter swirler setup and its ability to enhance properties such as shear for droplet breakdown or recirculation. The purpose of this project is to perform a cold flow analysis of a dual axial swirl combustion chamber, with axial air injection. The main aim of the thesis is to determine the effect on the flow field of a secondary counter-rotating swirler on the relevant parameters, such as the stagnation point; shear; recirculation and fuel to air mixing, in a combustor that can operate using either hydrogen or kerosene as fuel. During this research project, the methods of assessment are Computational Fluid Dynamics and Particle Image Velocimetry, which will provide clear and quantitative means of evaluating the flow behavior and its impact on the relevant parameters. The variables of this research project will be the geometric swirl number of the secondary swirler, the mass flow split and mass flow through the axial injection tube. The end result of this research project is to determine the influence these variables have on the relevant aforementioned parameters of combustion for several experimental points. This combustor setup may enable the future of aero engine combustion systems that can operate on different fuels, making it possible to balance some of the advantages and disadvantages of these propellants, while at the same time drastically reducing the CO2 and NOx emissions in order to meet the ACARE 2050 projections.