Transsonic Fan Pressure Ratio 1.7

The GasTurb LPC Standard Map has been generated on the basis of this data. The map tables you can download here are new interpretations of the same data. Moreover, they are extended down to lower spool speeds, too.

The ideas presented in GPPS-TC-2026-0083 are supported by this compressor map. 

About this fan

This fan is used as an example in a publication authored by C. Freeman and N.A. Cumpsty in a paper that discusses the flow phenomena in the rotor. Absolute efficiency is not given in that paper so it had to be guessed.

The only numbers known about the fan are the inlet hub-tip ratio (0.3) and the tip circumferential speed (456 m/s at standard day conditions).

 

References:

Jet Propulsion
A simple guide to the aerodynamics and thermodynamic design and performance of jet engines
Nicholas Cumpsty and Andrew Heyes
Cambridge University Press, Third Edition 2015

C. Freeman, N.A. Cumpsty
Method for the Prediction of Supersonic Compressor Blade Performance
Vol. 8, No. 1, Jan-Feb 1992
AIAA Journal Propulsion

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 variants are extrapolated down to 20% spool speed, which makes these maps suitable for simulating idle of high bypass ratio turbofans. The other two variants extend down to 1% spool speed. They are suited for both engine starting and windmilling simulations.

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