Experimental and numerical investigation of dual stage counter-rotating compressor

The performance and detailed flow structure of a counter-rotating compressor under design rotating speed and typical working condition were experimentally and numerically investigated. Numerical results show preliminarily that the total pressure ratio performance agreed with experimental data well, while the numerical peak efficiency was little higher than experimental one. The flow separation and great range low energy flow occur at the 10% span range of second rotor blade tip near stall point firstly, which was the main reason for the compressor stall. The second rotor worked at a large incidence angle (>5°)because of the separation at rotor one trailing edge.