Experimental investigation of advanced multistage casing treatments in a 2.5 stage high pressure compressor test rig

摘要

A two stage casing treatment was applied to a 2.5-stage axial compressor test rig and experimentally evaluated in terms of operability and local aerodynamics. The present study shows the impact of advanced casing treatments applied to both rotors of a compressor test rig, whose geometric and aerodynamic features are identical to those seen in the rear stages of an aircraft engine high pressure compressor. The casing treatment's impact on the local flow-phenomena, as well as their influence on the re-matching of the stage characteristics, is explained based on the experimental results presented. Furthermore, the performance of the compressor is analyzed. The data presented shows how multiple casing treatments are generally able to extend the surge margin and furthermore operate under the influence of rotating stall. The impact of each casing treatment on the local flow and the operation of the test compressor is explained. The present effort was conducted as part of the EU integrated program for New Aero Engine Core Concepts (NEWAC).