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

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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

Author(s):
Breugelmans, Frans A. E.
Author Organization(s):
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM) TURBOMACHINERY LAB
Descriptive Note:
Final rept. 1 Jul 71-30 Jun 72,
Supplementary Note:
See also Volume 2, AD-757 217.
Pagination:
0106

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
VKI-IN-42, ARL-73-0169
Contract/Grant Number(s):
AF-AFOSR-2104-71
Project Number(s):
AF-7065
Monitor Series:
73-0169
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*STALLING, INLET GUIDE VANES, FLOW FIELDS, COMPRESSOR COMPONENTS, CASCADE STRUCTURES, SUPERSONIC FLOW, BLEED SYSTEMS, BELGIUM
Field(s)/Group(s):
Jet and Gas Turbine Engines
Keyword(s):
Supersonic compressors
Report Date:
1972 Dec 01