Abstract:

For the curved leading edge shock surfaces generated by the high load swept axial rotors, using an analytical structure model of 3 D shock surface, this paper investigated the characteristics of the shock surface structure and calculated the distribution of the flow variables in front of and behind the shock. It focused on the influences of relatively forward or backward sweep rotors on the flow field behind but near the leading edge shock surface. By this analytical model, the paper answered one aspect of the question of the swept rotors' functions. For the first time, it quantitatively showed the existence of the phenomenon of 3 D shock induced spanwise and circumferential mixing.

Key words: high load axial compressor and fan, swept aer odynamics, shock structure, spanwise mixing