OEM’s are constantly looking for ways to address the conflicting requirement of reducing pollutant emissions, improving fuel burn and overall size of the propulsion system, without compromising the engine’s overall performance for both military and commercial propulsion systems. There is a global need to advance the propulsion system to deliver high thrust/power, high efficiency, low fuel burn i.e. reduce the specific fuel consumption with lower emissions. A promising technology being explored for this research work is axial staging of the combustion process to address this challenge, which operates with a conventional combustion chamber followed by reheated burner. The conventional gas turbine combustor has a main combustor where fresh air-fuel mixture is burnt while in a reheated burner, apart from main combustor, burnt products from the main combustor are again heated to high temperature to gain multifold benefits from this process. The objective of the current research work is to study the axial fuel staging in compact combustor through experimental and numerical investigation with detailed parametric variation of geometry and inlet conditions establishing key parameters (geometric & flow) to quantify efficacy of fuel staging, and its relationship to combustor geometry and performance parameters like, efficiency, profile & pattern factor, system pressure drops. The research work will focus on advancing the state of the art for axial fuel staged combustors using additive manufacturing technique, by exploring uniquely shaped combustors and fuel-air injection mechanisms and study the impact on the overall flow field for a practical application using liquid fuel injection.