A theory for the prediction of compressor blade aerodynamic response
A theory for the prediction of compressor blade aerodynamic response
复制标题
压气机叶片气动响应预测理论
DOI：
10.2514/6.1998-3308
复制
发表时间：
1998
影响因子：
27.7
通讯作者：
W. Cousins
中科院分区：
文献类型：
--
作者：
W. Cousins
压气机叶片对进口气流方向和速度突然变化的响应取决于局部气流条件和翼型的空气动力学设计。多年来，经验数据一直被用来描述动态叶片响应。压缩系统的最新动态模型和来自压缩机的高响应数据表明，压缩机叶片排对变化的入口条件的详细响应在所有压缩机中并不相同。当检查压气机对畸变进气道的响应时，观察结果表明，响应随畸变的周向程度而变化，并与压气机对周向动量场快速变化的响应能力有关。这些信息对于主动和被动稳定控制系统的设计和操作都是至关重要的。这项工作提出了一种方法，通过与进口速度图和设计叶片载荷特性的相关性来确定叶片排对周向动量场变化的响应。除了所提出的理论，一些数据和建议，为今后的工作。
The response of a compressor blade to sudden changes in inlet flow direction and velocity is governed by the local flow conditions and the aerodynamic design of the airfoil. For many years, empirical data has been used in an attempt to describe dynamic blade response. Recent dynamic models of compression systems and high-response data from compressors has shown that the detailed response of a compressor blade row to changing inlet conditions is not the same in all compressors. When examining the compressor response to a distorted inlet, observation shows that the response varies as a function of the circumferential extent of the distortion and is related to the ability of the compressor to respond to rapid changes in the circumferential momentum field. This information is critical to the design and operation of both active and passive stability control systems. This work proposes a method of determining blade row response to changes in the circumferential momentum field by correlation to the inlet velocity diagram and the design blade loading characteristics. In addition to the proposed theory, some data is presented and suggestions for future work are made.