An experience in development and implementation of measures for the axial compressor aerodynamic improve at the gas turbine unit for mechanical drive
The computational results of axial compressor operation are presented. The causes of unstable operation are described and recommendations for its improvement are worked out. It is defined that one of the main reason for unstable operation is mismatching of first and last group of compressor stages. In particular special attention were devoted to profiling of a fourth stage vane. Also the implementation results of suggested design are presented taken from real Gas Turbine Unit series of experiments.