压气机转子叶片的抑颤设计(“两机”专刊)

以一高压压气机转子叶片为对象开展了叶片抑颤工程设计方法研究，采用基于相位延迟边界条件的能量法和特征值法对原转子叶片模型的气动弹性稳定性进行评估，通过分析近失速工况下的非定常气动功密度分布，对叶片安装角沿径向分布、弦长和叶尖间隙等设计参数进行调整，以明确各参数对气动弹性稳定性的影响，最终达到提高气动阻尼的目的。研究结果表明：叶尖间隙对气动阻尼的影响较大，安装角次之，弦长影响相对较小。叶片气动阻尼随叶尖间隙的变化并非单调，而是存在一个叶尖间隙使其气动阻尼最小，即叶片气动弹性稳定性最差。减小进口气流攻角和增加折合频率，能够提高气动阻尼，设计中可以通过调节安装角来减小气流攻角，增加弦长来增大折合频率。

On the Design for Flutter Suppression of Rotor Blade in a Compressor

The design analysis for flutter suppression of a high pressure compressor rotor blade was investigated in this paper. The energy method based on the phase lagged boundary condition and the eigenvalue method were used to analyze the aeroelastic stability of the prototype blade under near stall condition. The effects of design parameters such as radial distribution of the blade stagger angle, chord length and tip clearance were investigated to clarify the influence and its extent of each parameter on the flutter, so as to improve the aerodynamic damping. The results show that the tip clearance has the greatest influence on aerodynamic damping, the stagger angle takes second place, and the chord length is the least. The variation of aerodynamic damping with tip clearance is not monotonous, so there exists a tip clearance to minimize the blade aerodynamic damping, where the blade aeroelastic stability is the worst. Reducing the attack angle and increasing the reduced frequency can improve the aerodynamic damping. In the design phase, the attack angle can be reduced by adjusting the stagger angle, and the reduced frequency can be increased by increasing the chord length.