Design and Testing of a High-Pressure-Ratio Centrifugal Stage – Probing the Aerodynamic & Mechanical Limits
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The paper describes the design, manufacture and testing of a novel high-pressure-ratio, single-stage centrifugal compressor targeted for use in high molecular weight applications. The stage was designed to deliver a minimum pressure ratio of 10:1 while also providing sufficient flow range to ensure stable operation, i.e., usable surge margin and overload capacity. The paper describes the motivation for the work, as well as the aerodynamic and mechanical design processes employed including a brief review of the analytical tools used. A high level overview of the aerodynamic optimization efforts is also presented. The paper provides an overview of the test compressor, instrumentation, test loop and the data acquisition system, and addresses the “shake-down” testing performed with a baseline configuration to establish feasibility, ground the analytical predictions, and identify potential oversights in the design. Test results from an enhanced design developed via aerodynamic optimization are also dis cussed. The paper closes with a review of the lessons learned and a summary of how the supersonic design extended the limits of what can be achieved with a centrifugal stage. Some thoughts regarding future work to enhance the performance of high-pressure-ratio stages and on the use of advanced optimization methodologies are also offered.
Sorokes, James; Lupkes, Kirk; Srinivasan, Ravi; Kuzdzal, Mark; Peer, Dave; Saretto, Silvano (2018). Design and Testing of a High-Pressure-Ratio Centrifugal Stage – Probing the Aerodynamic & Mechanical Limits. Turbomachinery Laboratory, Texas A&M Engineering Experiment Station. Available electronically from