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The transition from rotating stall to surge in an axial compressor.

机译：轴向压缩机从旋转失速过渡到喘振。

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摘要

This research investigated unsteady events such as stall inception, stall-cell development, and surge. Stall is characterized by a decrease in overall pressure rise and non-axisymmetric through-flow. Compressor stall can lead to surge which is characterized by quasi-axisymmetric fluctuations in mass flow and pressure. An expanded Greitzer model is presented to predict the stall and surge characteristics of a two-volume, two-throttle compression system. The current work provides a method to experimentally determine the time for a stall cell to fully develop after stall inception. This value is required for the model. Experimental stall and surge characteristics are compared to the predicted characteristics. Individual values of the upstream and downstream B parameter had the largest impact on the system dynamics for the compression system studied. The ending post-stall throttling point was found to influence the system dynamics in cases where the upstream and downstream value of B where close to the critical values.;Unsteady measurements of the flow field around the compressor rotor are examined. During the stall inception process, initial disturbances were found within the rotor passage near the tip region. As the stall cell develops, blade lift and pressure ratio decrease within the stall cell and increase ahead of the stall cell. The stall inception event and stall-cell development for stable rotating stall and surge were found to be nearly identical. A stalled compressor rotor can be considered to contain three main regions: stalled passages, recovering passages, and over-pressured passages. Over-pressured passages exhibit turning and pressure rise greater than pre-stall values.
机译：这项研究调查了不稳定事件，例如失速开始，失速细胞发育和激增。失速的特征在于总体压力上升和非轴对称通流减小。压缩机失速会导致喘振，喘振的特征是质量流量和压力的准轴对称波动。提出了扩展的Greitzer模型，以预测两体积，两油门压缩系统的失速和喘振特性。当前的工作提供了一种方法来实验确定失速开始后失速细胞完全发育的时间。该值对于模型是必需的。将实验失速和喘振特性与预测特性进行比较。对于所研究的压缩系统，上游和下游B参数的各个值对系统动力学的影响最大。在B的上游和下游值接近临界值的情况下，失速后的节流点被发现会影响系统动力学。检查了压缩机转子周围流场的不稳定测量结果。在失速开始过程中，在叶尖区域附近的转子通道内发现了初始干扰。随着失速室的发展，叶片升力和压力比在失速室中减小，并在失速室之前增加。发现失速开始事件和稳定旋转失速和喘振的失速单元发展几乎相同。失速的压缩机转子可被认为包含三个主要区域：失速通道，恢复通道和过压通道。超压通道的转弯和压力升高大于失速前的值。

著录项

  • 作者

    Hickman, Adam R.;

  • 作者单位

    University of Notre Dame.;

  • 授予单位 University of Notre Dame.;
  • 学科 Aerospace engineering.;Mechanical engineering.
  • 学位 Ph.D.
  • 年度 2017
  • 页码 116 p.
  • 总页数 116
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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