The effect of compressor exit measurement rake positions on performance assessment is quantified using a combined computational and experimental approach. The compressor under investigation consists of 4-stages and is representative of modern aero-engine core-compressors. The computational analysis is based on unsteady calculations of a 180-degree sector of the test compressor and experimental verification is provided by area-traverse data at two stations at the exit of the compressor.

It is shown that the exit rakes are subject to a circumferentially non-uniform flow caused by the combined effect of the potential field of the large struts in the compressor exit duct and the wakes originating from the outlet guide vanes. A circumferential stagger pattern, applied to the outlet guide vanes, designed to shield the upstream blade rows against the potential field of the large exit struts, is found to reduce the amplitude of the circumferential variation in stagnation pressure to half its original value and also shift its circumferential phase. The influence of the wakes from the outlet guide vanes is investigated by moving the rake instrumentation axially and by verniering it circumferentially over the pitch of the outlet guide vane. Recognizing that a smaller numerical model, consisting only of the rear compressor stage and the exit struts, is sufficient to capture the relevant flow mechanisms, the variation of the compressor exit correlations with the exit flow function is quantified.


Sensitivity of Multi-Stage Compressor Performance Assessment to Measurement Rake Positions

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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