| 摘要: |
| 为了提高跨声速压气机的气动弹性稳定性，针对跨声速颤振实验转子提出了栅距交替非谐布局方案，基于能量法建立了其全周气动阻尼计算模型，数值研究了栅距非谐对气动阻尼的影响。计算了谐调转子的气动性能、颤振边界和叶片模态，其结果和实验数据吻合较好，比较了谐调及非谐转子气动性能，发现栅距非谐会造成转子气动性能有所降低，随着非谐量的增加，性能降低越明显；在研究的非谐条件下，压比最大相对降低0.30%，效率最大降低0.54%。对于该转子的平均气动阻尼，栅距非谐使得转子在大部分甚至整个叶片间相角区域内气动阻尼均有所提高，最大达到37%。通过对叶片表面不同叶高的非定常压力以及积分气动力研究表明，栅距交替非谐对转子相邻两个叶片稳定性的影响存在差异，并且非谐量越大，差异越明显。 |
| 关键词: 栅距非谐 气动阻尼 颤振 能量法 气动弹性稳定性 |
| DOI： |
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| 基金项目:国家自然科学基金重点资助项目(60934001)。 |
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| Effects of Pitch Mistuning on Rotor Damping of Transonic Compressor |
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YANG Xiao-dong1,HOU An-ping2,LI Man-lu3,LIU Ma-cheng2
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(1. Beijing Electro-Mechanical Engineering Institute，Beijing 100074，China;2. National Key Laboratory of Science and Technology on Aero-Engines Aero-Thermodynamics，
School of Energy and Power Engineering，Beihang University，Beijing 100191，China;3. AVIC Academy of Aeronautic Propulsion Technology，Beijing 101304，China)
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| Abstract: |
| Based on transonic compressor flutter test rotor，a pitch mistuning method is investigated to improve the aeroelastic stability of transonic compressor. The effects of pitch mistuning on rotor aerodynamic damping are obtained based on energy method with a full-annulus aerodynamic damping computational model. Numerical results of rotor performance，flutter margin and blade mode of tuned rotor are respectively consistent with experiment results. Compared with results of tuned rotor，pitch mistuning leads to lower aerodynamic performance and this tendency becomes more significant as mistuning level increases，and the maximum decline of pressure ratio and efficiency is 0.30% and 0.54% respectively，while average damping increases during most inter-blade phase angles(IBPA) with a maximum increase of 37%.Investigation of unsteady aerodynamic pressure and integral aerodynamic forces shows that pitch mistuning affects aeroelastic stability of adjacent blades differently，and the differences become more apparent with a high-level mistuning. |
| Key words: Pitch mistuning Aerodynamic damping Flutter Energy method Aeroelastic stability |
