The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume III.
Final rept. 1 Jul 71-30 Jun 72,
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM) TURBOMACHINERY LAB
Pagination or Media Count:
The report describes the test results of a supersonic axial-flow compressor stage with a tip Mach number of 2.0. Volume 2 discusses a method to eliminate the inlet problem. Volume 3 describes the overall and detailed performance of the original model FB III with an interblade row bleed system. The bleed area represents 10 of the inlet area and a minimum bleed flow of 7 of the total inlet flow could be achieved. The stage performance data are presented for the 60 to 107 N over the square root of theta of the nominal speed. Author
- Jet and Gas Turbine Engines