In order to study the influence of probe blockage effect on the test performance of the compressor, a full-channel steady simulation method was used to establish a regression model of the influence of the probe on the compressor performance. Taking NASA Rotor67 and Stage35 compressor as research objects, different sizes and quantities of probes are arranged at different axial positions of the compressor inlet and outlet respectively, the flow-efficiency and flow-pressure ratio characteristic line are obtained under different probe blockage ratios, circumferential and axial layouts at the design speed. The calculation results show that due to the blockage effect of the probe, the flow rate of the blocking point is reduced, the flow rate of the stall point is increased, the efficiency and pressure ratio of the compressor are decreased, and the change of the airflow angle caused by the probe is the main cause of the above change. The response surface model was used to model the regression of the data, and the regression model of the compressor characteristics in the presence/absence of the probe was obtained, and the regression model was verified. The relative error was within 5%, indicating the established regression model of probe on the influence of  compressor performance has good accuracy.

Keywords: compressor, probe, blockage effect, full channel, steady, regression model


Influence of Probe Blockage Effect on Compressor Test Performance

Division / Sponsor:
International Gas Turbine Institute (IGTI)

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

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