Accession Number:

AD0875902

Title:

Radial Outflow Compressor Component Development. Phase IV. Test Results

Descriptive Note:

Final rept. May 1969-Mar 1970

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP

Personal Author(s):

Report Date:

1970-09-01

Pagination or Media Count:

88.0

Abstract:

The purpose of the Phase IV program was to obtain high-speed performance data for the optimum circular inlet vane position and stator vane settings. The only difference from the Phase III configuration was a change made to the rotating diffuser area schedule. The circular inlet vane position had little effect on rotor performance. The recontoured rotating diffuser provided some improvement in rotor pressure ratio and efficiency relative to Phase III data. Maximum rotor performance was obtained with a supersonic stator setting of 83.4 degrees. Best stator system performance was obtained with a supersonic stator setting of 79 degrees. Maximum stage performance was obtained with a supersonic stator setting of 82 degrees.

Subject Categories:

  • Hydraulic and Pneumatic Equipment
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE