A theoretical design of a tubular type gas turbine combustor design was carried out in this paper in aerodynamic design point of view. Aerodynamic design processes plays a vital role in the design and performance of gas turbine combustion systems. With good aerodynamic design and good matching fuel-injection system, a trouble free combustor design may be arrived. By considering the inlet parameters such as pressure, temperature, density and air mass flow rate of a combustor, a design process was carried out. Design process involves the geometric dimensional calculations of various geometries in a combustor like casing cross-sectional area and its length, linear cross-sectional area and its length, swirler design calculations, etc. Thermodynamically, ideal constant pressure process takes place inside a combustor.