Investigation of influence of rotational speed and pressure ratio on performance of two-stage counter-rotating compressor

In this paper, we investigate the aerodynamic performance and flowfield of a double row counter-rotating axial compressor using the streamline curvature method. The aim is to study the influence of the rotational speed and pressure ratio on some parameters of two counter-rotating rotors, which include exit velocity, flow angle and diffusion factor. In the full paper, we explain in some detail our method of investigation, the calculation results and their analysis. In this abstract, we just add some pertinent remarks to listing the two topics of explanation. The first topic is: brief introduction to what we investigate and the method of calculation. The second topic is: the analysis of calculation results. In this topic, we use three subtopics to analyze the calculation results. In subtopic 2.1, Fig. 4 through Fig. 9 indicate that, when the rotational speed of Rotor 2 is kept constant and the rotational speed of Rotor 1 decreases, the exit velocity and flow angle increase, while the diffusion factor of Rotor 2 decreases. In subtopic 2.2, we use Figs. 10-15 to show that, with the increase of the pressure ratio of Rotor 1, the diffusion factor at the exit of Rotor 2 decreases. In subtopic 2.3, Figs. 16-21 demonstrate that, with the change of the rotational speed of the two rotors, the adjustment of its pressure ratio can remarkably improve the flowfield at the exit of the rotor. The calculation results show preliminarily that the large difference between two rotors' rotational speeds can bring about the separation or distortion of flowfield.