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Gas flow nonuniformity is one of the main sources of rotor blade vibrations in the gas turbine engines. Often, the source of the flow circumferential nonuniformity are the annular frames, located in the flow passage of the engine. This leads to the increased dynamic stresses in rotor blades and consequently to the blade destruction. The goal of the research was to find an acceptable method of reducing the level of gas flow nonuniformity. Thus, this study gives the ideas about methods of improving the flow structure in gas turbine engine. It allows the selection of the most suitable method for reducing gas flow nonuniformity.

Strategy for Reduction of the Negative Effects of Circumferential Flow Irregularity in Axial Compressor