External CAD view of a small-scale turbojet engine showing the outer casing and glow plug locations used for combustor ignition during startup. Assumes axisymmetric geometry, rigid mounting of external components, negligible casing deformation, and convective heat transfer to ambient air under nominal operating conditions.

Sectioned CAD model of the turbojet engine illustrating the internal flow path and major components, including inlet, compressor, annular combustor, turbine, and exhaust nozzle. Assumes steady-state operation, uniform inlet flow, ideal component alignment, and adiabatic flow through rotating components with convective heat loss in the combustor and nozzle.

Preliminary CAD model of the annular combustor liner showing primary, secondary, and dilution hole patterns used for fuel–air mixing and flame stabilization. Assumes nominal mass flow distribution across zones, uniform liner material properties, convectively cooled walls, and preliminary hole sizing based on empirical jet-in-crossflow correlations in the absence of validated combustion performance data.