【摘要】：在不同氣動工況、不同幾何模型下,采用自行開發(fā)程序?qū)θh(huán)多排的高壓壓氣機進行了流固耦合數(shù)值模擬,分析了進口導流葉片(IGV,以下簡稱導葉)對轉(zhuǎn)子葉片顫振穩(wěn)定性的影響。通過對氣動彈性標準算例4的數(shù)值模擬驗證了程序在顫振領域的有效性。針對導葉-轉(zhuǎn)子模型和單轉(zhuǎn)子模型,考察了近堵塞點、近設計點和近失速點3個工況下,節(jié)徑變化對葉片顫振穩(wěn)定性的影響,給出了氣動彈性最不穩(wěn)定狀態(tài)對應的葉片振動形式。通過對比發(fā)現(xiàn),導葉作用隨工況而異,近堵塞點導葉使得轉(zhuǎn)子1階彎曲模態(tài)氣動阻尼提高130.63%。研究表明:導葉引起的非定常壓力波反射增強了轉(zhuǎn)子葉片的非定常壓力擾動幅值,使得彎曲振型的顫振穩(wěn)定性增強�；趩无D(zhuǎn)子模型的顫振分析給出了不準確的氣動阻尼值。
[Abstract]:Under different aerodynamic conditions and different geometry models, the fluid-solid coupling numerical simulation of high-pressure compressor with full ring and multiple rows was carried out by using self-developed program, and the inlet guide vane (IGV,) was analyzed. The influence of guide vane on the flutter stability of rotor blade. The effectiveness of the program in flutter field is verified by numerical simulation of Aeroelastic standard example 4. For guide vane rotor model and single rotor model, the effects of nodal diameter variation on blade flutter stability were investigated under three operating conditions: near clogging point, near design point and near stall point. The vibration form of blade corresponding to the most unstable state of Aeroelasticity is given. By comparison, it is found that the guide vane action varies with the working conditions, and the aerodynamic damping of the rotor in the first order bending mode is increased by 130.63 because of the near clogging point guide vane. The results show that the unsteady pressure wave reflection caused by the guide blade enhances the amplitude of the unsteady pressure disturbance of the rotor blade and enhances the flutter stability of the bending mode. Based on the flutter analysis of a single rotor model, an inaccurate aerodynamic damping value is given.
【作者單位】： 先進航空發(fā)動機協(xié)同創(chuàng)新中心;北京航空航天大學能源與動力工程學院;
【分類號】：V232.4

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