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- W4312687590 abstract "Abstract The identification of stall inception mechanisms and stability-limiting components in a centrifugal compressor is required for development of effective surge suppression approaches. Part 1 of this two-part paper investigates the surge signature of a centrifugal compressor at subsonic, transonic, and supersonic inlet tip conditions, and Part 2 considers the relationship of the surge signature with the compressor static pressure characteristics as well as the impeller leading edge relative tip Mach number. Experiments were performed in the Single Stage Centrifugal Compressor (SSCC) facility at Purdue University with both steady performance and dynamic pressure data recorded. Results show the presence of both mild and deep surge on the compressor map. Deep surge occurs at subsonic and supersonic impeller tip relative Mach numbers while mild surge is observed as the tip relative Mach number nears unity. Long length-scale modal oscillations can be detected only at the transonic operating condition while spike disturbances are identified as the precursor to instability at subsonic and supersonic tip relative Mach numbers. Finally, the impeller is determined to be the origin of instability throughout most of the compressor map. The observation of impeller-induced instability refreshes the conventional understanding that the diffuser is typically the stability-limiting component for centrifugal compressors with vaned diffusers and suggests various surge suppression approaches may be necessary to achieve range extension throughout a compressor map." @default.
- W4312687590 created "2023-01-05" @default.
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- W4312687590 date "2022-06-13" @default.
- W4312687590 modified "2023-09-27" @default.
- W4312687590 title "Investigation of Surge in a Transonic Centrifugal Compressor With Vaned Diffuser: Part 1 – Surge Signature" @default.
- W4312687590 doi "https://doi.org/10.1115/gt2022-82682" @default.
- W4312687590 hasPublicationYear "2022" @default.
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