Abstract The present paper provides a summary of investigations of the tip air injection, which has been studied for over 30 years to extend the stall margin in axial flow compressors. The review covers the design of injected parameters, understanding of stability-enhancing mechanism, application of active control, and self-recirculation based on tip air injection. First, the injected parameters that can influence the stability-enhancing capability are surveyed and classified. These include injected mass flow and momentum, structure, pitch and yaw angle, axial location, and circumferential distribution. Next, the effect of tip air injection on the internal flow field is introduced; the action on the main stream flow or tip leakage flow depends on the injected moment ratio. Finally, the applications of active control with tip air injection and self-recirculating injection from a single-rotor to multi-stage compressors are listed and discussed. The active control methods are based on the Moore–Greitzer model and online prediction of stall inception. This study aims to aid researchers who are working on stability enhancement with tip air injection in compressors to improve their work. Moreover, considering that the regulation of injected mass flows or momentums is flexible, this study would facilitate the immediate application of the tip air injection in actual aero-engine compressors.

中文翻译：

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改进轴流压缩机失速裕度的尖端空气喷射综述

摘要 本文对叶尖空气喷射的研究进行了总结，该研究已经研究了 30 多年，以延长轴流压缩机的失速裕度。综述涵盖了注入参数的设计、稳定性增强机制的理解、主动控制的应用以及基于尖端空气注入的自循环。首先，对影响稳定性增强能力的注入参数进行调查和分类。这些包括注入的质量流量和动量、结构、俯仰角和偏航角、轴向位置和圆周分布。接下来介绍尖端空气喷射对内部流场的影响；对主流流或尖端泄漏流的作用取决于注入力矩比。最后，列出并讨论了带有尖端空气喷射和自循环喷射的主动控制从单转子到多级压缩机的应用。主动控制方法基于 Moore-Greitzer 模型和失速开始的在线预测。这项研究旨在帮助致力于通过压缩机中的尖端空气喷射来增强稳定性的研究人员改进他们的工作。此外，考虑到喷射质量流量或动量的调节是灵活的，这项研究将促进尖端空气喷射在实际航空发动机压缩机中的直接应用。这项研究旨在帮助致力于通过压缩机中的尖端空气喷射来增强稳定性的研究人员改进他们的工作。此外，考虑到喷射质量流量或动量的调节是灵活的，这项研究将促进尖端空气喷射在实际航空发动机压缩机中的直接应用。这项研究旨在帮助致力于通过压缩机中的尖端空气喷射来增强稳定性的研究人员改进他们的工作。此外，考虑到喷射质量流量或动量的调节是灵活的，这项研究将促进尖端空气喷射在实际航空发动机压缩机中的直接应用。