小型軸向壓縮機氣動參數變異之葉片結構分析

陳精一 ； 余仁方

《中華民國振動與噪音工程學會論文集》 1995 (1995/06) Pp. 101-110

https://doi.org/10.30028/CSSVANNUAL.199506.0101

摘要

本研究擬開發一具1000lb推力之渦輪引擎為目標，進行整合設計分析工作，以完成一套國人自行設計、製造與測試之動力系統，以供未來大型研發工作參考。壓縮機的設計過程中，可由氣動理論及經驗公式，求得最佳化之葉片與流道，以滿足設計的需求，然而一個完整的設計工作必須配合不同的領域相結合，方能成為一個完整的設計。由氣動力的葉形設計考慮上，採用23個葉片數、中間葉弦疊層、長方形徑線輪廓、均勻負載、傾斜角度為零的設計分析基準。本結構分析將分葉片模組及葉片轉盤模組，以了解兩種模組之間的差異，每一模組將進行穩態應力分析及振動模態分析、及坎貝圖分析以了解其振動特性。基於氣動設計的考慮，葉片的結構分析將可分為下列幾項：葉片數目、葉弦疊層位置、徑線輪廓、負載分佈、傾斜效應、厚度效應。由分析的結果可知，最大穩態應力合乎材料的容許應力。兩個模組平約應力中除第一層有較大的差異外，其餘五層的差異均在4%以內。自然頻率中，兩個模組前四個模態僅有4％的差異。坎貝圖的分析顯示葉片模組和葉片轉盤模組相似，避開前三倍的基本轉速，而第二自然頻率和4/REV有相交現象。因此，該葉片的設計須進一步修正。由以上結果得知，葉片模組能夠提供合理的分析結果。

並列摘要

The goal of this study is to integrated design and analysis a compressor which base on 1000 lb thrust of the engine. The optimal blade shape and the flow field can be derived from the aerodynamic theory and the experience formulation in the compressor design process. But the overall design has to consider the different field such as structure strength, manufacture and assembly, etc. The basic design in this study is base on 23 blades, middle chord stacking, rectangular meridional profile, constant load and zero lean.
Two modules are created in this blade structural analysis. One is the blade module and the other is the blade-disk module. Both modules perform static and dynamic analysis. According to the aerodynamic design, the following parameters are considered: number of blades, blade chord stacking, blade meridional profile, load distribution, lean effect and thickness effect. From the analysis results, the maximum static stress is satisfied the allowable stress of the material. Except the first layer, the variation of average stress from second layer to sixth layer is 4% difference between the two modules. Due to the boundary condition, there is big difference in the first layer. However, the maximum average stress does not occur at the first layer. The variation of the natural frequency between the two modules is 4% difference in the first four modes. The Campbell diagram analysis shows that no resonance condition in the first three per rev. But the second natural frequency is crossing with the fourth per rev. It is necessary to further modify the blade design. In views of the small variation in both modules, the blade module is sufficiently enough in the analysis of blade structure at this point.