随着变循环航空发动机向宽工况、高效率和高可靠性方向发展，涡轮叶片所承受的载荷不断提高，大展弦比低压涡轮叶片气动弹性问题日益突出。本文以宽速域低压涡轮转子叶片为研究对象，系统开展了气弹稳定性评估与抑颤设计。首先，基于有限元方法分析了转子叶片在不同工况下的振动特性，考查了冷却腔及叶冠结构对叶片固有频率和振型的影响。在此基础上，对最大亚巡航与设计工况下前两阶模态的气动阻尼特性进行了对比分析。结果表明：在最大亚巡航工况下，叶片整体表现为气弹稳定状态；然而在气动负荷更大的设计工况下，转子叶片前两阶模态在特定节径处存在负气动阻尼，其中第一阶模态在-7节径处气动阻尼比最小，为-0.108%，第二阶模态在18节径处阻尼比最小，为-0.046%，存在气弹失稳风险。进一步分析冷却腔和叶冠结构发现，叶冠会显著改变叶片的振型和频率分布，从而有效提高气动阻尼水平、实现抑颤设计。最后，在振型差异较大的低节径模态，利用基于移相条件的能量法进行计算与验证。本文研究结果可为下一代宽速域、变循环发动机的低压涡轮气动弹性安全性分析与结构优化设计提供重要参考。
With the development of variable cycle aero-engines towards wider operating conditions, higher efficiency, and greater reliability, the loads on turbine rotor blades are continuously increasing, and their aeroelastic stability problems are becoming increasingly prominent. This study takes a wide-speed-range low-pressure turbine rotor blade as the research object, and systematically carries out aeroelastic stability assessment and flutter suppression design. First, based on the finite element method, the vibration characteristics of the rotor blade under different operating conditions are analyzed, and the influence of the cooling cavity and shroud structure on the blade's natural frequency and mode shape is investigated. On this basis, a comparative analysis of the aerodynamic damping of the first two modes under maximum subsonic cruise and design conditions is performed. The results show that under the maximum subsonic cruise condition, the blade row exhibits a stable state. However, under the design conditions with greater aerodynamic loads, the first two modes of the rotor blade have negative aerodynamic damping at specific nodal diameters (ND). Among them, the first mode has the smallest aerodynamic damping ratio at the -7 ND, which is -0.108%, and the second mode has the smallest damping ratio at the 18 ND, which is -0.046%, indicating a risk of aeroelastic instability. Further analysis of the cooling cavity and shroud structure reveals that the shroud can significantly change the blade's mode shape and frequency distribution, thereby effectively improving the aerodynamic damping level and achieving flutter suppression design. Finally, for low ND modes with large mode shape differences, the energy method based on phase shift conditions is used for calculation and verification. The research results of this study can provide an important reference for the aeroelastic safety analysis and structural optimization design of low-pressure turbines in the next generation of wide-speed-range, variable cycle engines.
[1]王强, 郑日恒, 陈懋章.航空发动机科学技术的发展与创新[J].科技导报, 2021, 39(03):59-70
[2]刘治呈.变循环发动机发展综述[J].现代制造技术与装备, 2019, 55(1):177-179
[3]MEYER C L, SMITH I D, BLOOMER H E.Performance of a turbojet engine with adjustable first-stage turbine stator and variable-area exhaust nozzle[R]. NACA-RM E52104, 1953.
[4]高杰, 郑群, 岳国强, 等.燃气轮机变几何涡轮气动技术研究进展[J].中国科学:技术科学, 2018, 48(11):1141-1150
[5]赵首源, 周逊, 罗磊, 等.变循环发动机高压涡轮可调导叶对涡轮级气动性能的影响[J].热能动力工程, 2025, 40(09):55-65
[6]郑源林, 郭仕博.航空发动机涡轮叶片气动性能优化与热交换技术研究[J].电子元器件与信息技术, 2025, 9(06):61-64
[7]李卓轩.燃气轮机涡轮叶片寿命预测研究[D].沈阳航空航天大学, 2024.DOI:10.27324/d.cnki.gshkc.2024.000428.
[8]杨晓飞, 孙太璐, 孟德君, 等.兼顾多模式的核心机驱动风扇级气动设计方法[J].航空学报, 2024, 45(02):82-89
[9]Hwang S, Son C, Seo D, et al.Comparative study on steady and unsteady conjugate heat transfer analysis of a high pressure turbine blade[J].Applied Thermal Engineering, 2016, 99(/):765-775
[10]Hylton L D, Mihec M S, Turner E R, et al.Analytical and experimental evaluation of the heat transfer distribution over the surfaces of turbine vanes[R]. NASA-CR-168015, 1983.
[11]朱兴丹, 谭晓茗, 郭文, 等.高压涡轮转子叶片内部气流组织方式研究[J].航空学报, 2014, 35(12):3273-3282
[12]郑赟, 杨慧, 田晓.振荡压气机叶栅叶片表面非定常响应以及气弹稳定性分析[J].振动与冲击, 2012, 31(03):111-116
[13]Carta F.O. Coupled Blade-Disk-Shroud Flutter Instabilities in Turbojet Engine Rotor[J].Journal of Engineering for Gas Turbines and Power, 1967, 89(3):419-426
[14]Bendiksen O.O. Aeroelastic Problems in Turbomachines[A]. Proceedings of the 31st Structure, Structural Dynamics and Materials Conference[C]. AIAA Publishing House, 1990: 1736-1761.
[15]Moffatt S., He L. Blade Forced Response Prediction for Industrial Gas Turbines: Part 1-Methodologies[A]. Proceedings of the ASME Turbo Expo: Power for Land, Sea, and Air[C]. American Society of Mechanical Engineers, 2003, 36878: 407-414.
[16]韩乐, 王延荣.转子叶片气弹稳定性与强迫响应分析[J].航空发动机, 2021, 47(04):82-90
[17]Erdos J.I.,Alzner E,McNally W. Numerical Solution of Periodic Transonic Flow through a Fan Stage[J].AIAA Journal, 1977, 15(11):1559-1568
[18]He L.An Euler Solution for Unsteady Flows Around Oscillating Blades[J].Journal of Turbomachinery, 1990, 112(4):714-722
[19]Guo Tongqing, Zhou Di, Lu Zhiliang.A Double - passage Shape Correction Method for Predictions of Unsteady Flow and Aeroelasticity in Turbomachinery[J].Advances in Applied Mathematics and Mechanics, 2017, 9(4):839-860
[20]Hall K.C.,Thomas JP.,Clark W. S. Computation of Unsteady Nonlinear Flows in Cascades Using a Harmonic Balance Technique[J].AIAA Journal, 2002, 40(5):879-886
[21]Thomas J.P.,Dowell EH.,Hall K. C. Nonlinear Inviscid Aerodynamic Effects on Transonic Divergence,Flutter,and Limit-Cycle Oscillations[J].AIAA Journal, 2002, 40(4):638-646
[22]Zhao X.Han L,Wei D. Efficient Study on the Influence of Compressor Casing Configuration on Aeroelastic Stability Using Multi-Passage Energy Method[J].Propulsion and Power Research, 2025, 14(2):243-258
[23]张小伟.叶轮机械叶片气动弹性稳定性数值预测方法研究[D].北京：北京航空航天大学, 2011.
[24]付志忠.叶轮机械叶片流致振动数值预测方法研究[D].北京：北京航空航天大学, 2016.
[25]张小博.航空轴流转子叶片气动弹性数值模拟[D].北京：北京航空航天大学, 2018.
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