Single Stage Transsonic Compressor - Design Pressure Ratio 1.5
This map of a compressor with forward-swept rotor blades and a pressure ratio of 1.5 may be usefull for modeling the fan of a very high bypass ratio turbofan.
This compressor map serves as the basis for Figure5 in GPPS-TC-2026-0083.
About this compressor
The map is based on the measured data reported by Stephan Kablitz in his thesis, which was published in 2003 at the Technical University of Darmstadt in Germany. The title of his thesis is "The impact of forward sweep on the tip gap flow of transonic axial compressors".
Design Point Data:
| Mass Flow [kg/s] | 16 |
| Pressure Ratio | 1.5 |
| Circumferential speed [m/s] | 400 |
| Rotational speed [rpm] | 20.000 |
| Tip Diameter [m] | 0.38 |
| Radius Radio | 0.51 |
| Tip Mach Number | 1.35 |
Figures of the measured data and two smooth map versions
Tables for use with performance programs
The map tables are available in four variants:
- KablitzThesisBasicGasTurb.txt
- KablitzThesisExtendedGasTurb.txt
- KablitzThesisBasicNPSS.txt
- KablitzThesisExtendedNPSS.txt
Note that the file extension must be changed to MAP after downloading if you want to use the map with GasTurb.
Additional figures from my experimental map smoothing program
