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首页> 外文期刊>Progress in Aerospace Sciences >Review of tip air injection to improve stall margin in axial compressors
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Review of tip air injection to improve stall margin in axial compressors

机译：审查尖端空气喷射以改善轴向压缩机的失速裕度

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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.
机译：本文提供了对尖端空气喷射研究的总结，该研究已经进行了30多年的研究，以扩展轴流式压缩机的失速裕度。这篇综述涵盖了喷射参数的设计，对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喷射的自我再循环。首先，对可能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，俯仰和偏航角，轴向位置和周向分布。接下来，介绍尖端空气注入对内部流场的影响；对主流流量或尖端泄漏流量的作用取决于注入的力矩比。最后，列出并讨论了从单转子到多级压缩机的尖端空气喷射和自循环喷射主动控制的应用。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在压缩机中注入尖端空气来提高稳定性的研究人员改善他们的工作。此外，考虑到喷射质量流量或动量的调节是灵活的，该研究将有助于尖端空气喷射在实际的航空发动机压缩机中的立即应用。

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