In order to explore the performance and three-dimensional flow characteristics of axial compressor rotors at low Reynolds number,the aerodynamic performance and internal flow field of transonic rotor compressor Rotor37 at ground and high altitude were numerically simulated.The results show that at an altitude of 20 km,the total pressure ratio and adiabatic efficiency of the compressor near the stall point are reduced by 8.0%and 5.3%,respectively,and the surge margin is reduced by 3.1%.At low Reynolds numbers,at the flow separation position on the suction surface of the rotor,the flow mixing will be in advance and more intense,resulting in an increase in the separation boundary layer.At the same time,due to the thicker surface boundary layer,the interaction between the shock wave and the boundary layer is strengthened,which reduces the pressure component of the upward movement of the low-energy fluid in the boundary layer of the blade surface.The low-energy fluid is more likely to migrate to the vicinity of the blade tip under the action of centrifugal force,which may be an important factor triggering the instability of the rotor.At low Reynolds numbers,the suction surface of the blade root completely separates at 84%of the axial chord length and forms a corner vortex,and a shedding vortex is formed during its movement to the tip of the blade.The area of the corner vortex and the shedding vortex increases significantly,which is one of the important reasons for the decrease in the working efficiency of the rotor at low Reynolds numbers.
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