Six-Stage High Pressure Compressor
This compressor is the result of a joint compressor research program, which was carried out by the Chinese Aviation Industry Corp. (AVICI and AVICII) and Rolls-Royce Deutschland Ltd. (RRD).
The ideas presented in GPPS-TC-2026-0083 are supported by this compressor map.
About this compressor
It is a modern high-pressure compressor with a comparatively high stage loading that achieved a pressure of 8 on the compressor rig. It has variable guide vanes.
Design Data
| Max pressure ratio @ 100% | 8.58 |
| Mass flow [kg/s] | 18.78 |
| Inlet hub-tip ratio | 0.7 |
| Relative rotor 1 tip Mach number | 1.13 |
Reference:
Design and Test Demonstration of the JET01 Six-Stage High-Pressure Compressor
Cheng Ronghui, Ulrich Wenger, Lan Faxiang, Xin Tian
ISABE 2007-1184
Figures of the measured data and the smooth map
Tables for use with performance programs
The map tables are available in four variants. The first two maps have been extended to 30% spool speed, and the second two to 1%.
- ISABE2007_1184_Fig29_Extnd03GasTurb.txt
- ISABE2007_1184_Fig29_Extnd03NPSS.txt
- ISABE2007_1184_Fig29_Extnd001GasTurb.txt
- ISABE2007_1184_Fig29_Extnd001NPSS.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
