Semester Thesis — TU Munich, Chair of Turbomachinery and Flight Propulsion
A Python-based workflow for parametric generation of centrifugal compressor impeller geometry, built on NASA's PyTurbo framework and extended with a custom hub and shroud contour generation function.
The source code was developed within a TUM thesis project and is not public. This repository documents the workflow, methodology, and generated geometry results.
The tool follows a two-stage design process:
Stage 1 — Meanline design (Python): A station-wise meanline solver computes the one-dimensional aerothermodynamics of the compressor at inlet, impeller exit, vaneless space (with iterative convergence), and diffuser exit. The output includes the velocity triangles at each station, exported with visualization for design review.
Stage 2 — 3D geometry generation (PyTurbo): The meanline results feed a parametric 3D geometry build. Blade angles, chord distributions, thickness distributions, and radial positions are controlled programmatically. A custom extension to PyTurbo generates the hub and shroud contours that define the meridional flow passage.
The handoff between stages is user-guided, keeping the designer in control of the design decisions between meanline sizing and 3D geometry.
- Station-wise meanline solution with velocity triangle visualization
- Parametric blade sections interpolated across the span into smooth 3D surfaces
- Hub and shroud meridional contours via the custom PyTurbo extension
- Full 3D impeller geometry for visualization and design inspection
Additional geometry visualizations are in the Results/ directory.
Parametric, script-driven geometry generation enables rapid design iteration and lays the groundwork for integration into automated aerodynamic and CFD workflows, where geometry must regenerate consistently from a small set of design parameters.
- NASA PyTurbo: github.com/nasa/pyturbo-aero