Scholarlink

<p>Controllable speed casing (CSC) represents an innovative development in casing treatment technology, wherein the traditional stationary casing is reconfigured into two components: a rotatable ring and a stationary ring. Initial position (IP) of the rotatable ring is a critical parameter affecting the operational effectiveness of CSC. This study investigates the influence of varying IP of the rotatable ring on the aerodynamic performance and flow stability of a high-load compressor stage, with terminal position (TP) fixed at the rotor tip trailing edge. The results reveal that positioning the rotatable ring near the rotor tip trailing edge leads to moderate improvements in stability by controlling the secondary flow at the trailing edge. However, when IP coincides with the region where the tip leakage vortex and induced vortex breakdown, CSC disrupts the upstream flow, increasing the blockage of low-energy fluid, thereby precipitating an early stall in the compressor. Conversely, positioning IP at the rotor leading edge enables CSC to effectively manage tip leakage flow, facilitating the deflection of the tip leakage vortex away from the adjacent blade pressure surface. This adjustment mitigates the blocking effect within the blade tip passage, thereby significantly enhancing the compressor’s flow stability. Under these optimal conditions, CSC achieves a substantial 45.11% improvement in stable operating margin of the compressor.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Influence of the Initial Position of the Controllable Speed Casing on the Tip Flow of High-Load Compressor Stage

  • 期刊论文

  • 发表日期：

    2025年12月17日

查看全文
  • Wanyang Wu,
  • Yi Hu,
  • Ao Zhao,
  • Jingjun Zhong

摘要

Controllable speed casing (CSC) represents an innovative development in casing treatment technology, wherein the traditional stationary casing is reconfigured into two components: a rotatable ring and a stationary ring. Initial position (IP) of the rotatable ring is a critical parameter affecting the operational effectiveness of CSC. This study investigates the influence of varying IP of the rotatable ring on the aerodynamic performance and flow stability of a high-load compressor stage, with terminal position (TP) fixed at the rotor tip trailing edge. The results reveal that positioning the rotatable ring near the rotor tip trailing edge leads to moderate improvements in stability by controlling the secondary flow at the trailing edge. However, when IP coincides with the region where the tip leakage vortex and induced vortex breakdown, CSC disrupts the upstream flow, increasing the blockage of low-energy fluid, thereby precipitating an early stall in the compressor. Conversely, positioning IP at the rotor leading edge enables CSC to effectively manage tip leakage flow, facilitating the deflection of the tip leakage vortex away from the adjacent blade pressure surface. This adjustment mitigates the blocking effect within the blade tip passage, thereby significantly enhancing the compressor’s flow stability. Under these optimal conditions, CSC achieves a substantial 45.11% improvement in stable operating margin of the compressor.