Effect of rotor CLOCKING on blade aerodynamic load in compressor stages.

The field of three stages in axial compressor for a gas turbine was simulated by the unsteady calculation method based on harmonics. The impact of CLOCKING effect of rotor blade in second stage on aerodynamic load of static blade in mid stage was investigated. By analyzing the wake transportation of flow field and the unsteady aerodynamic loads of the blades, the result shows that the different CLOCKING of R2 rotor blade corresponds to different entropy transportation characteristic, so the aerodynamic load discrepancy of each blade row is significantly obvious under different flow induced force. When at the CLK2 position, the aerodynamic force of static blade is always positive. In addition, its amplitude of fluctuation is smaller than that of the other location, the range of direction angle is also small, and the amplitude of fluctuation for aerodynamic torque and the changing number of direction are smaller than those of other locations, therefore the most stable aerodynamic load is obtained. [ABSTRACT FROM AUTHOR]