Design and Test of an Experimental Rotating Diffuser Centrifugal Compressor Test Rig

Format:

Conference/Event

Author/Creator:

Rodgers, C., author.

Conference Name:

Aerospace Engineering and Manufacturing Meeting (1976-11-30 : San Diego, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1976

Summary:

The mechanical and performance test evaluation of an experimental high pressure ratio single-stage centrifugal compressor incorporating a rotating vaneless-vaned diffuser is discussed. The test rig employed was a turbodrive configuration with the centrifugal impeller driven by a directly-coupled air turbine. The rotating diffuser was supported on a separate shaft operating at approximately 25% impeller speed and directly coupled to a high-speed water brake. Mechanical operation of the compressor rig was satisfactory. Best overall test performance achieved at design speed was a total-total pressure ratio of 7.7 with an adiabatic efficiency of 72.3% (average stage exit Mach number of 0.27). A broad flow range ratio of 1.25 between choke and surge was obtained with the diffuser rotating at design speed

Notes:

Vendor supplied data

Publisher Number:

760927

Access Restriction:

Restricted for use by site license