Accession Number:

AD0752585

Title:

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

Descriptive Note:

Final rept. 1 Jul 71-30 Jun 72,

Corporate Author:

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

Personal Author(s):

• Breugelmans,Frans A. E.

Report Date:

1972-06-01

Pagination or Media Count:

51.0

Abstract:

The report describes the test results of a supersonic axial flow compressor stage with a tip Mach number of 2.0. Volume I discusses especially the inlet stall, the associated flow field and the stage performance. Methods are proposed to eliminate the stall problem. Author

Descriptors:

• (*AXIAL FLOW COMPRESSORS
• STALLING)
• COMPRESSOR ROTORS
• COMPRESSOR STATORS
• SUPERSONIC FLOW
• FLOW FIELDS
• CASCADE STRUCTURES
• PRESSURE
• PERFORMANCE(ENGINEERING)

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE