进口探针支杆尾迹诱发压气机转子叶片共振的数值研究

doi:10.13675/j.cnki.tjjs.190797

推进技术 ›› 2021, Vol. 42 ›› Issue (5): 1002-1012.DOI: 10.13675/j.cnki.tjjs.190797

进口探针支杆尾迹诱发压气机转子叶片共振的数值研究

杨荣菲¹，刘氦旭¹，向宏辉²，高杰²，王靖宇³

1.南京航空航天大学能源与动力学院，江苏南京 210016;2.中国航发四川燃气涡轮研究院，四川绵阳 621000;3.四川大学空天科学与工程学院，四川成都 610065

出版日期:2021-05-15 发布日期:2021-08-15
基金资助:
民用飞机专项科研项目（MJ-2016-J-96）。

Numerical Study of Compressor Rotor Blade Resonance Induced by Wake of Inlet Probe Support

1.College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China;2.AECC Sichuan Gas Turbine Establishment，Mianyang 621000，China;3.School of Aeronautics and Astronautics，Sichuan University，Chengdu 610065，China

Online:2021-05-15 Published:2021-08-15

摘要/Abstract

摘要： 为了探究包含支杆直径10mm进口探针的压气机罕见地出现第一级转子叶片动应变超限报警的产生机理，以更换直径8mm+3mm的探针后报警解除的情况作为对比方案，开展了进口探针支杆诱发压气机转子叶片振动的流动机理研究。以试验压气机为研究对象，利用ANSYS APDL命令流语言使用载荷步文件法对该压气机转子叶片进行了单向瞬态流固耦合数值计算。结果表明，两类探针支杆尾迹影响下，压气机转子叶片都发生了共振；引起叶片共振的激振力频率来源于支杆尾迹诱导频率与支杆通过频率的叠加，其中支杆尾迹诱导频率是由支杆尾迹涡脱落与转子叶片通过非同相位所诱导产生；支杆直径减小，支杆尾迹引起的叶片表面激振力减小，使叶片振动应变相应降低。

关键词: 进口探针支杆;压气机;叶片共振;流固耦合;支杆尾迹涡

Abstract: In order to find out the mechanism of the first stage rotor blade dynamic strain over limit alarm rarely occurred in a compressor with a diameter of 10mm inlet probe，the flow mechanism of the compressor rotor blade vibration induced by the inlet probe support was studied by comparing the alarm release after replacing the 8mm + 3mm diameter probe.Taking the experimental compressor as the research object， the unidirectional transient fluid structure interaction numerical calculation of the compressor rotor blade is carried out by using the load step file method in ANSYS APDL command language.The results show that the compressor rotor blade resonates under the influence of two kinds of probe strut wake， and the frequency of the excitation force that causes the blade resonance comes from the superposition of the wake induction frequency of the strut and the passage frequency of the strut， in which the wake induction frequency of the strut is caused by the vortex shedding of the strut and the passage of the rotor blade through the non-homogeneous phase. As the diameter of the strut decreases， the exciting force on the blade surface caused by the wake of the strut decreases， and the vibration strain of the blade decreases accordingly.

Key words: Inlet probe support;Compressor;Blade resonance;Fluid-structure interaction;Strut wake vortex

杨荣菲，刘氦旭，向宏辉，高杰，王靖宇. 进口探针支杆尾迹诱发压气机转子叶片共振的数值研究[J]. 推进技术, 2021, 42(5): 1002-1012.

YANG Rong-fei¹, LIU Hai-xu¹, XIANG Hong-hui², GAO Jie², WANG Jing-yu³. Numerical Study of Compressor Rotor Blade Resonance Induced by Wake of Inlet Probe Support[J]. Journal of Propulsion Technology, 2021, 42(5): 1002-1012.

参考文献

[1] 李少辉. 探针支杆对压气机下游流场的影响［D］. 北京：北京航空航天大学， 2013.
[2] Simon Coldrick， Paul Ivey， Roger Wells. Considerations for Using 3-D Pneumatic Probes in High-Speed Axial Compressors［J］. Journal of Turbomachinery， 2003， 125（1）： 149-154.
[3] Jan Lepicovsky. Effects of a Rotating Aerodynamic Probe on the Flow Field of a Compressor Rotor［R］. NASA/CR-2008-215215.
[4] Xiang Honghui， Ge Ning， Hou Minjie， et al. An Experimental Investigaton of the Effects of Upstream Probe Disturbance on Compressor Cascade Performance［J］. Proc IMechE Part G： J Aerospace Engineering， 2017， 231（7）： 1248-1257.
[5] 杨荣菲，赵建通，向宏辉，等. 进口探针支杆对1.5级压气机气动性能的影响［J］. 推进技术， 2017， 38（5）：1038-1046.
[6] Coldrick S， Ivey P C， Wells R G. The Influence of Compressor Aerodynamics on Pressure Probes， Part 2： Numerical Models［R］. ASME GT 2004-53241.
[7] Herwart Hoenen， Robert Kunte， Phillip Waniczek， et al. Measuring Failures and Correction Methods for Pneumatic Multi-Hole Probes［R］. ASME GT 2012-68113.
[8] Christoph Sanders， Marius Terstegen， Magnus H?lle， et al. Numerical Studies on the Intrusive Influence of a Five-Hole Pressure Probe in a High-Speed Axial Compressor［R］. ASME GT 2017-63399.
[9] 吴森林，胡骏，向宏辉，等. 小型探针在小尺寸压气机性能试验中的应用［J］. 燃气涡轮试验与研究，2011， 24（4）： 40-43.
[10] 高杰，向宏辉，杨荣菲，等. 尾缘修型对探针支杆尾迹抑制作用的数值研究［J］. 燃气涡轮试验与研究， 2017， 30（1）： 28-31.
[11] 杨荣菲，赵建通，向宏辉，等，一种用于消减探针支杆绕流尾迹的罩型薄板结构［P］. 中国专利： 106482929， 2017-03-08.
[12] Zhou Xuedong， Mitch Wolff J. Transonic Compressor IGV/Rotor Interaction Analysis Including Fluid Structure Interaction［R］. AIAA 2004-5292.
[13] Zhang M， Tsukamoto H. Unstready Hydrodynamic Forces Due to Rotor-Stator Interaction on a Diffuser Pump with Identical Number of Vanes on the Impeller and Diffuser［J］. Journal of Fluids Engineering， 2005， 127（4）： 743-751.
[14] Mingming Zhang， Anping Hou， Sheng Zhou， et al. Analysis on Flutter Characteristics of Transonic Compressor Blade Row by a Fluid-Structure Coupled Method［R］. ASME GT 2012-69439.
[15] Carstens Volker， Kemme Ralf， Schmitt Stefan. Coupled Simulation of Flow-Structure in Teraction in Turbomachinery［J］. Aerospace Science and Technology， 2003， 7（4）： 298-306.
[16] Sadeghi M， Liu F. Coupled Fluid-Structure Simulation for Turbomachinery Blade Rows［R］. AIAA 2005-18.
[17] Zdravkovich M M. Review of Interference-Induced Oscillations in Flow Past Two Parallel Circular Cylinders in Various Arrangements［J］. Journal of Wind Engineering and Industrial Aerodynamics， 1988， 28（1-3）： 183-199.
[18] Benra F K， Dohmen H J， Pei J. A Comparison of One-Way and Two-Way Coupling Methods for Numerical Analysis of Fluid-Structure Interactions［J］. Journal of Applied Mathematics， 2011，（7）： 1-16.
[19] S?rensen Niels N， Bechmann Andreas， Zahle Frederik. 3D CFD Computations of Transitional Flows Using DES and a Correlation based Transition model［J］. Windenergy， 2011， 14（1）： 77-90.
[20] 杨庆生. 现代计算固体力学［M］. 北京：科学出版社， 2007.
[21] Achenbach E. Distribution of Local Pressure and Skin Friction Around a Circular Cylinder in Cross-Flow up to Re=5×10⁶［J］. Journal of Fluid Mechanics， 1968， 34（4）.

进口探针支杆尾迹诱发压气机转子叶片共振的数值研究

Numerical Study of Compressor Rotor Blade Resonance Induced by Wake of Inlet Probe Support

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