Accession Number:

AD0781592

Title:

Continued Development-Two Stage High-Pressure-Ratio Centrifugal Compressor

Descriptive Note:

Final rept.

Corporate Author:

SOLAR TURBINES INTERNATIONAL SAN DIEGO CA

Personal Author(s):

• Rodgers, Colin

Report Date:

1974-04-01

Pagination or Media Count:

41.0

Abstract:

The report presents the results of a continued compressor technology program directed toward development of a small, advanced, two-stage centrifugal compressor designed to attain high pressure ratios with fixed geometry. Extensive compressor performance data were obtained for two test configurations. The second test configuration, incorporating a minor rematch to the first-stage compressor components, and operating at a design speed of 82,000 rpm, gave a peak adiabatic efficiency of 78 with a pressure ratio of 13.2 and a corrected airflow of 1.94 pps. The compressor exhibited extremely wide flow ranges between surge and choke, with peak efficiencies away from the surge line.

Descriptors:

• *CENTRIFUGAL COMPRESSORS
• *GAS TURBINES
• BLEED SYSTEMS
• DIFFUSERS
• EXPERIMENTAL DESIGN
• HIGH PRESSURE COMPRESSORS
• IMPELLERS
• SHROUD RINGS
• SURGES

Subject Categories:

• Hydraulic and Pneumatic Equipment
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE