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本文采用理论分析和数值模拟的方法对预压缩型超音压气机叶栅的气动性能进行了分析研究。结果表明,叶栅通道中的预压缩波可以有效地降低叶栅自起动所需的最小喉口/进口面积比,改善起动性能;随进口马赫数的降低,预压缩波由与前缘弓形激波压力面分支相交将变为与吸力面分支相交;当预压缩波与前缘弓形激波吸力面分支相交后,前缘驻点流线与叶片吸力面之间的流道宽度将随进口马赫数的降低而变窄,使得进口气流角增大。
In this paper, the aerodynamic performance of precompression-type supersonic compressor cascade is analyzed by theoretical analysis and numerical simulation. The results show that the pre-compression wave in the cascade passage can effectively reduce the minimum throat / inlet area ratio required for starting the cascade and improve the starting performance. With the decrease of the inlet Mach number, The intersection of the pressure surface and the branch will become intersect with the suction surface branch; when the pre-compression wave and the leading edge of the arcuate shock surface after the intersection of the suction surface, the leading edge of the stagnation streamline and the suction surface of the flow path width with the inlet Mach The number of narrow and narrow, making the import flow angle increases.