Control of Blade Flutter by Smart-Casing Treatment
Control of Blade Flutter by Smart-Casing Treatment
复制标题
DOI：
10.2514/2.5770
复制
发表时间：
2001-03
影响因子：
1.9
通讯作者：
Xiaofeng Sun;X. Jing;Hongwu Zhao
中科院分区：
文献类型：
--
作者：
Xiaofeng Sun;X. Jing;Hongwu Zhao
介绍了一种新型的阻抗可调声学衬管作为压气机叶片噪声抑制的机匣处理方法。数值结果表明，波纹升力系数和力矩系数随腔体深度和偏压马赫数的变化规律。从这些结果可以看出，在给定的压气机工作状态下，不同阻抗的衬板对压气机叶片输出有正有负的影响。然而，可以通过数值方法找到与特定工况相匹配的抑制叶片噪声的最优阻抗值。相应的，可以得到在任何给定的压缩机工况下，确定腔体深度和偏低马赫数控制值的两条曲线。通过这些控制曲线，提出了采用前馈控制方法实现压气机叶片叶片主动控制的可行性。与现有的叶片叶片控制方法相比，智能机匣处理确实展示了一种全新的叶片叶片控制理念。术语Aab =叶片周边Ab =叶片上表面或下表面a0 =声速b =叶片半弦CFqi；CF®i =叶片升力系数的虚部CFqr；CF®r =叶片升力系数CMqi实部；CM®i =叶片力矩系数的虚部CMqr；CM®r =叶片力矩系数的实部G =格林函数G！=格林函数对时间的傅里叶变换
A novel acoustic liner with adjustable impedance is introduced as a casing treatment to suppress compressor blade e utter. Numerical results are presented to show the variation of the e uctuating lift and moment coefe cients as functions of the liner cavity depth and the bias-e ow Mach number through the orie ces of the liner. It can be seen from these results that liners with different impedances would have an either positive or negative effect on compressor blade e utter under a given compressor working condition. However, an optimal impedance value that matches a specie c working condition to suppress the blade e utter can be found by a numerical method. Correspondingly, two curves that determine the control values of liner cavity depth and bias-e ow Mach numbers underanygivencompressorworkingconditioncanbeobtained.Bymeansofthesecontrolcurves,itisproposedthat the active control of compressor blade e utter may be realized by a feedforward control methodology. Compared with the existing methods for the control of blade e utter, smart-casing treatment indeed shows a novel conception of blade e utter control. Nomenclature Aab = periphery of a blade Ab = the upper or lower surface of a blade a0 = speed of sound b = blade semichord CFqi;CF®i = imaginary part of blade lift coefe cient CFqr;CF®r = real part of blade lift coefe cient CMqi;CM®i = imaginary part of blade moment coee cient CMqr;CM®r = real part of blade moment coefe cient G = the Green’ s function G! = Fourier transform of the Green’ s function for time