Three Stage Transsonic Compressor
This map of a 3-stage axial compressor with a pressure ratio of 4 may be usefull for modeling the booster of a geared turbofan.
This compressor map serves as the basis for Figures 9 and 10 in GPPS-TC-2026-0083.
About this compressor
This compressor map is found in the NASA report TP-2597, figure 18. This figure shows the map of the first three stages, in which the IGV and stators are in their design position.
Design data for the first three stages:
| Mass Flow [kg/s] | 29.7 |
| Pressure Ratio | 4.47 |
| Circumferential speed [m/s] | 430.3 |
| Rotational speed [rpm] | 16020 |
| Tip Diameter [m] | 0.513 |
| Radius Radio | 0.488 |
Figures of the measured data and the smooth map
Tables for use with performance programs
The map tables are available in two variants:
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
