Accession Number:

AD0770648

Title:

The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume III.

Descriptive Note:

Final rept. 1 Jul 71-30 Jun 72,

Corporate Author:

VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM) TURBOMACHINERY LAB

Personal Author(s):

• Breugelmans,Frans A. E.

Report Date:

1972-12-01

Pagination or Media Count:

106.0

Abstract:

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

Descriptors:

• *STALLING
• INLET GUIDE VANES
• FLOW FIELDS
• COMPRESSOR COMPONENTS
• CASCADE STRUCTURES
• SUPERSONIC FLOW
• BLEED SYSTEMS
• BELGIUM

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE