This multi-stage turbojet engine model was created using Siemens NX to explore turbomachinery layout, internal assembly packaging, and blade geometry scaling. The conceptual model features an axial flow architecture consisting of a single intake fan, a 3-stage compressor section, a central combustion chamber, and a 2-stage turbine exhaust.
The engine layout is broken down into four core sections along the main shaft axis:
- Intake Section: A single large intake fan stage designed for initial air capture.
- Compression Section: A 3-stage axial compression system to model pressure reduction/volume decrease.
- Combustion Chamber: A central burner housing surrounding the inner shaft casing.
- Turbine / Exhaust Section: A 2-stage turbine layout designed for expansion.
To maintain geometric consistency across the rotating stages, a unified aerofoil profile was created and parametrically scaled in diameter and chord length across the compression and turbine stages. I also added internal stator guide vanes after each turbine to try and counteract some of the rotation.
This model served as a conceptual exercise in CAD modelling, assembly hierarchy, and mechanical packaging within Siemens NX. While non-functional from a real-world aerodynamic and thermodynamic perspective (due to using identical aerofoil profiles across varying stages), it provided valuable practice in multi-body packaging and complex stage geometry alignment.
In a future revision or iteration of this concept, I plan to incorporate variable aerofoil profiles optimised specifically for high-pressure compression vs. expansion turbine dynamics, as well as improving internal stator guide vanes.