Compressor rotor,
This paper reports the digital scientific research on the initial stall of compressor rotor.
NASA rotor -67, by using the whole flow channel in the calculation.
NASA rotator -67, it is estimated that all the wheels have been used.
In order to trigger the rotating stall, one of the blades increased the surface roughness.
The surface roughness of a blade increases, resulting in rotating stall.
At the beginning of stall, the tip clearance vortex is far away from the suction surface of the adjacent blade on the upper part of the rough blade, which leads to the vortex rupture.
At the beginning of stall, the vortex in the tip clearance leaves the suction surface above the rough blade, which leads to the weakening of the vortex.
It is found that the stall mass propagates in the opposite direction to the rotation direction of the blade at about 30% rotation speed.
It is found that the stall zone propagates in the opposite direction to the blade at an angular velocity of about 30%.
The influence of bleed air on compressor stability is also studied in this paper.
This paper also studies the exhaust effect of a stable compressor.
The average mass flow discharged from the relief valve is 65438+ 0.2% of the main flow.
The average mass flow discharged by the exhaust valve is 65438+ 0.2% of the main flow.
It was found that this amount of bleeding effectively suppressed stall disturbance.
This emission discovery can effectively suppress the stall problem.
Key words: transonic axial compressor, NASA rotor -67, stall initiation, deflation, rotating stall.
Key words: transonic axial compressor-NASA rotor -67 rotating stall at the initial stage of stall.