ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Aerodynamic load of multistage vaneless counterrotating turbine under wake/shock rotor/rotor interactions
Received date: 2024-04-23
Revised date: 2024-04-28
Accepted date: 2024-05-31
Online published: 2024-06-17
Supported by
National Natural Science Foundation of China(52336002);National Science and Technology Major Project（J2019-Ⅱ-0011-0031）
To investigate the impact of wake/shock on the aerodynamic load distribution of downstream turbine blades in a multi-stage vaneless counter-rotating turbine， unsteady numerical simulation was utilized to analyze the influence of complex inter-stage flow on pressure fluctuation on the downstream blade surfaces. The study reveals that in the multi-stage vaneless counter-rotating turbine， all guide vanes are eliminated， resulting in suction side of the first-stage moving blade with an extended uncovered section. The extended uncovered suction side forms a converging-diverging wake flow passage resembling a Laval nozzle in interaction with the wake from adjacent blades. Under the unsteady interaction between the stages， the exit Mach number of the first-stage moving blade decreases， leading to the formation of a new compression wave （wake flow passage shock） near the trailing edge of the suction side of the first-stage moving blade superimposed on the existing suction side trailing edge shock. At specific moments within one cycle， both the reflected shock and the wake flow passage shock act on the 28.8% axial position on the suction side of the second-stage moving blade leading to a significant increase in pressure fluctuation peak value at that location. The peak value reaches 81.2% of the peak value induced by the suction side trailing edge shock sweeping， indicating that the suction side trailing edge shock is the primary factor causing pressure load variations on the blade surface of the second-stage moving blade. The main perturbation region for pressure fluctuation induced by the suction side trailing edge shock wave is the leading edge of the second-stage moving blade， with the maximum peak value of pressure fluctuation in this region within one cycle reaching 47.7% of the mean pressure. Due to the dissipation effects of the reflected shock of pressure side trailing edge shock and wake flow passage shock， the wake strength of the first-stage moving blade significantly decreases， resulting in a minor impact on the aerodynamic load distribution on the blade surface of the second-stage moving blade. Frequency analysis results indicate that due to the combined effects of the wake flow passage shock and the reflected shock of pressure side trailing edge shock， the main frequency of pressure fluctuation on the blade surface of the second-stage moving blade is twice the sweeping frequency of the suction side trailing edge shock.
Zhihao ZHU , Xiuming SUI , Jian PU , Long HAO , Wei ZHAO , Qingjun ZHAO . Aerodynamic load of multistage vaneless counterrotating turbine under wake/shock rotor/rotor interactions[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(24) : 630582 -630582 . DOI: 10.7527/S1000-6893.2024.30582
| 1 | 周庆晖， 赵巍， 隋秀明， 等. 零预旋涡轮动叶吸力面无遮盖段内凹型线激波损失抑制方法研究［J］. 工程热物理学报， 2022， 43（4）： 939-944. |
| ZHOU Q H， ZHAO W， SUI X M， et al. A shock loss reduction method for a zero inlet swirl turbine rotor using a suction side concave profile［J］. Journal of Engineering Thermophysics， 2022， 43（4）： 939-944 （in Chinese）. | |
| 2 | 张磊. 超高负荷跨音速涡轮气动设计理论及其非定常流动特性研究［D］. 北京： 中国科学院研究生院（工程热物理研究所）， 2011. |
| ZHANG L. Investigation of aerodynamic design method and unsteady flow characteristics of ultra-highly loaded turbine［D］. Beijing： Institute of Engineering Thermophysics，Chinese Academy of Sciences， 2011 （in Chinese）. | |
| 3 | 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（4）： 82-90. |
| HAN L， WANG Y R. Analysis of aeroelastic stability and forced response of rotor blades［J］. Aeroengine， 2021， 47（4）： 82-90 （in Chinese）. | |
| 4 | 洪杰， 张大义， 陈璐璐. 气流激励下的叶片高周疲劳寿命研究的发展［J］. 航空动力学报， 2009， 24（3）： 652-661. |
| HONG J， ZHANG D Y， CHEN L L. Review on investigation of high cycle fatigue failures for the aero engine blade［J］. Journal of Aerospace Power， 2009， 24（3）： 652-661 （in Chinese）. | |
| 5 | ZHAO B， QI M X， SUN H， et al. A comprehensive analysis on the structure of groove-induced shock waves in a linear turbine［J］. Aerospace Science and Technology， 2019， 87： 331-339. |
| 6 | DE′NOS R， ARTS T， PANIAGUA G， et al. Investigation of the unsteady rotor aerodynamics in a transonic turbine stage［J］. Journal of Turbomachinery， 2001， 123（1）： 81-89. |
| 7 | 杨策， 刘尚涛， 老大中， 等. 可调导叶向心涡轮转子叶片压力波动激励机制［J］. 工程热物理学报， 2014， 35（1）： 38-41. |
| YANG C， LIU S T， LAO D Z， et al. Variable guide vanes radial turbine blade surface pressure fluctuation excitation mechanism［J］. Journal of Engineering Thermophysics， 2014， 35（1）： 38-41 （in Chinese）. | |
| 8 | LIU J， QIAO W Y， DUAN W H. Effect of bowed/leaned vane on the unsteady aerodynamic excitation in transonic turbine［J］. Journal of Thermal Science， 2019， 28（1）： 133-144. |
| 9 | 季路成， 黄海波， 陈江， 等. 涡轮中的激波/叶排相互作用［J］. 工程热物理学报， 2002， 23（2）： 163-166. |
| JI L C， HUANG H B， CHEN J， et al. Shock wave/blade interaction in transonic turbine［J］. Journal of Engineering Thermophysics， 2002， 23（2）： 163-166 （in Chinese）. | |
| 10 | PENG W， REN X D， LI X S， et al. Influence of position of intake struts on unsteady load and vibration of first-stage rotor［J］. Machines， 2022， 10（11）： 1096. |
| 11 | MAO X C， LIU B. A numerical study on the unsteady effect of axial spacing on the performance in a contra-rotating axial compressor［J］. Proceedings of the Institution of Mechanical Engineers， Part C： Journal of Mechanical Engineering Science， 2017， 231（14）： 2598-2609. |
| 12 | QU X， ZHANG Y J， LU X G， et al. Unsteady influences of blade loading distribution on secondary flow of ultra-high-lift LPT［J］. Aerospace Science and Technology， 2020， 96： 105550. |
| 13 | 赵庆军， 王会社， 赵晓路， 等. 无导叶对转涡轮三维流场的非定常数值模拟［J］. 工程热物理学报， 2006， 27（1）： 35-38. |
| ZHAO Q J， WANG H S， ZHAO X L， et al. Numerical analysis of 3-d unsteady flow in a vaneless counter-rotating turbine［J］. Journal of Engineering Thermophysics， 2006， 27（1）： 35-38 （in Chinese）. | |
| 14 | ZHAO W， WU B， XU J Z. Aerodynamic design and analysis of a multistage vaneless counter-rotating turbine［J］. Journal of Turbomachinery， 2015， 137（6）： 061008. |
| 15 | BIAN X T， WANG Q S， SU X R， et al. Interaction mechanisms of shock waves with the boundary layer and wakes in a highly-loaded NGV using hybrid RANS/LES［J］. Chinese Journal of Aeronautics， 2020， 33（1）： 149-160. |
| 16 | 肖大启， 郑赟， 杨慧. 轴向间距对转子叶片气动激励的影响［J］. 航空动力学报， 2012， 27（10）： 2307-2313. |
| XIAO D Q， ZHENG Y， YANG H. Effect of axial spacing on aerodynamic excitation of rotor blade［J］. Journal of Aerospace Power， 2012， 27（10）： 2307-2313 （in Chinese）. | |
| 17 | LAUMERT B， MA?RTENSSON H， FRANSSON T H. Investigation of unsteady aerodynamic blade excitation mechanisms in a transonic turbine stage-part II： Analytical description and quantification［J］. Journal of Turbomachinery， 2002， 124（3）： 419-428. |
| 18 | LAUMERT B， MA?RTENSSON H， FRANSSON T H. Investigation of unsteady aerodynamic blade excitation mechanisms in a transonic turbine stage-part I： Phenomenological identification and classification［J］. Journal of Turbomachinery， 2002， 124（3）： 410-418. |
| 19 | 高丽敏， 苗芳， 李瑞宇， 等. 动/动干涉效应对叶片非定常负荷的影响［J］. 航空学报， 2014， 35（7）： 1874-1881. |
| GAO L M， MIAO F， LI R Y， et al. Effect of rotor/rotor interactions on blades unsteady loading［J］. Acta Aeronautica et Astronautica Sinica， 2014， 35（7）： 1874-1881 （in Chinese）. | |
| 20 | 邹正平， 叶建， 张永新， 等. 非定常流动对叶片表面负荷分布影响的数值模拟研究［J］. 燃气涡轮试验与研究， 2006， 19（1）： 21-26. |
| ZOU Z P， YE J， ZHANG Y X， et al. Numerical simulation of unsteady flow effects on turbine blade loading distributions［J］. Gas Turbine Experiment and Research， 2006， 19（1）： 21-26 （in Chinese）. |
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