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<p>In order to improve the stability of a supercritical CO<sub>2</sub> (sCO<sub>2</sub>) centrifugal compressor, numerical simulations were conducted to analyze the relationship between tip clearance sizes and the internal flow characteristics and stable operating range under near-stall conditions. The results demonstate that, as the tip clearance reduces, the total pressure ratio and the isentropic efficiency both increase. When the tip clearance reaches 0.005 mm, the compressor shows the best overall performance, and its stable operating range is relatively wide. The tip leakage flow merges into the main flow, leading to tip leakage vortices. The flow separation and leakage flow cause overflow and backflow at the blade’s leading edge, resulting in flow path blockage. This is the main reason for aerodynamic stall in the compressor. With tip clearance of 0 mm, the compressor’s performance drops instead. Friction between the fluid in the impeller and the casing reduces the near-wall fluid velocity. As a result, blade wall vortices form in the flow passage, disrupting the flow and causing blockage, which ultimately leads to compressor stall.</p>

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Effect of tip clearance on the instability of supercritical CO2 centrifugal compressors

  • 期刊论文

  • 发表日期：

    2026年4月9日

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  • Zhiting Tong,
  • Xinxia Liu,
  • Xiaomin Yang,
  • Yue Zhang

摘要

In order to improve the stability of a supercritical CO2 (sCO2) centrifugal compressor, numerical simulations were conducted to analyze the relationship between tip clearance sizes and the internal flow characteristics and stable operating range under near-stall conditions. The results demonstate that, as the tip clearance reduces, the total pressure ratio and the isentropic efficiency both increase. When the tip clearance reaches 0.005 mm, the compressor shows the best overall performance, and its stable operating range is relatively wide. The tip leakage flow merges into the main flow, leading to tip leakage vortices. The flow separation and leakage flow cause overflow and backflow at the blade’s leading edge, resulting in flow path blockage. This is the main reason for aerodynamic stall in the compressor. With tip clearance of 0 mm, the compressor’s performance drops instead. Friction between the fluid in the impeller and the casing reduces the near-wall fluid velocity. As a result, blade wall vortices form in the flow passage, disrupting the flow and causing blockage, which ultimately leads to compressor stall.