Test of an Axial Compressor Stage Designed for a Total Pressure Ratio of Three to One

reportActive / Technical Report | Accession Number: AD0778844 | Open PDF

Abstract:

Complete experimental results are presented from tests of a supersonic axial-compressor stage designed for a tip speed of 1600 ftsec, a stage total pressure ratio of 3.0 and an inlet hubtip radius ratio of 0.75. At design speed, the compressor passed 70 percent of design flow, achieved a stage total pressure ratio of 2.25, and achieved isentropic efficiencies of 0.74 for the rotor and 0.61 for the stage. This poor performance was attributed to an excessive increase of rotor deviation angle as rotor incidence increased at part speed. A proposed solution to this problem is described.

Author(s):
Wennerstrom, Arthur J. ; Frost, George R. ; Derose, Robert D.
Author Organization(s):
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OH
Descriptive Note:
Technical rept.
Pagination:
0433

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release, Document Partially Illegible
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited. Document Partially Illegible.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
ARL-74-0001
Task Number(s):
706504
Project Number(s):
AF-7065
Monitor Series:
HDL
 Subject Terms
Joint Capability Areas:
JCA_5_Command and Control; JCA_5.3_Planning; JCA_4.7.2_Installation Services; JCA_4.7_Base and Installations Support; JCA_6_Net Centric; JCA_6.1.3_Switching and Routing; JCA_1.2.5_Lessons Learned; JCA_6.1.1_Wired Transmission; JCA_5.6.1_Assess Compliance with Guidance; JCA_5.6_Monitor; JCA_6.1_Information Transport; JCA_6.4.1_Secure Information Exchange
Communities of Interest:
C4I
Descriptor(s):
*AXIAL FLOW COMPRESSORS, *TURBOMACHINERY, DIFFUSION, DYNAMIC PRESSURE, COMPRESSOR ROTORS, GAS TURBINES, COMPUTER PROGRAMS, SUPERSONIC FLOW
Field(s)/Group(s):
Jet and Gas Turbine Engines
Report Date:
1974 Jan 01