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

PDF Url : AD0781592

Report Date : Apr 1974

Pagination or Media Count : 41

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