The Influence of Compressor Inlet Guide Vane /Stator Relative Circumferential Positioning on Blade Wake Transport and Interaction.

摘要

A periodically sampling hot-wire measurement system was used to obtain numerous periodic-average (Electronically and arithmetically averaged values of periodically sampled data) three-dimensional velocity vector data for flow through the first stage (inlet guide vane, rotor, and stator rows) of a low-speed, multistage, axial-flow research compressor. New data are presented for the maximum noise circumferential position of the first stator blade row. Comparisons are made between these data and similar data previously acquired and reported for the minimum noise configuration of the compressor. The inlet guide vane (IGV) wake avenue was found to interest first stator row blades at two span locations, one near the hub and the other near the tip, for maximum noise and at only one span location, near mid-span, for minimum noise. This difference in IGV wake / stator leading edge intersection patterns resulted in variations of the first stator exit flow deviation angle near the hub and tip portions of the compressor annulus. These variations were explained in terms of the larger fluctuations of stator inlet flow associated with the inlet guide vane wake avenues.