Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions

Hongzhi CHENG; Mingyang WANG; Chuangxin ZHOU; Shengfeng ZHAO; Xingen LU; Junqiang ZHU

doi:10.13224/j.cnki.jasp.20210134

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Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions

Turbomachinery | 更新时间：2025-04-07

- Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions
- Journal of Aerospace Power Vol. 37, Issue 2, Pages: 283-295(2022)
- 作者机构：
  
  1.中国科学院工程热物理研究所轻型动力重点实验室，北京 100190
  2.中国科学院大学工程科学学院，北京 100049
  3.中国科学院轻型动力创新研究院，北京 100190
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210134
  CLC：
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Hongzhi CHENG, Mingyang WANG, Chuangxin ZHOU, et al. Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions[J]. Journal of Aerospace Power, 2022, 37(2): 283-295.
DOI：

Hongzhi CHENG, Mingyang WANG, Chuangxin ZHOU, et al. Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions[J]. Journal of Aerospace Power, 2022, 37(2): 283-295. DOI： 10.13224/j.cnki.jasp.20210134.

摘要

以某1.5级高负荷轴流压气机为研究对象，采用经过校核的数值模拟手段详细探究了低雷诺数下表面粗糙度对其气动性能及内部流场的影响。结果表明：相比于光滑叶片，表面粗糙度为137.8时压气机性能提升最为明显，总压比、堵塞流量以及峰值效率分别提升4.01%、2.24%、5.34%。在整个表面粗糙度大小范围内，表面粗糙度布置在吸力面前缘至50%轴向位置时对分离、转捩的调控效果较好，能够较大限度地提升低雷诺数下压气机的气动性能。表面粗糙度通过促进转捩、抑制层流分离以及改变速度和静压分布来改善压气机流场和气动特性，同时一定程度上恶化了后面级的级间匹配关系，造成静子叶根处分离提前，角区分离加剧，限制了压气机整体气动性能的进一步提高。

Abstract

Numerical investigations were conducted to investigate the effects of the surface roughness on the aerodynamic performance of a 1.5⁃stage highly⁃loaded axial compressor under low Reynolds number conditions.Results showed that the highest aerodynamic performance improvement was achieved at surface roughness 137.8.The maximum increase in total pressure ratio，blocking flow，and peak efficiency was 4.01%，2.24%，and 5.34%，respectively.Detailed analysis showed that，within the entire region of surface roughness magnitudes，the surface roughness covering from leading edge to the 50% axial chord length on the suction surface had a relatively evident advantage to control the separation and transition，and the aerodynamic performance of compressor at low Reynolds number conditions was improved more distinctly.In general，at low Reynolds number，surface roughness can promote the transition，suppress the laminar flow separation，and change the overall magnitudes and distributions of the velocity and the static pressure，which improved the flow field and performance.However，it also deteriorated the incoordination between the subsequent stages，which induced a stronger corner separation in the aft stator，and limited the further improvement of the overall aerodynamic performance of the compressor.

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references

BALJE O E . A study on Reynolds number effects in turbomachines [J]. Journal of Engineering for Power , 1964 , 86 （ 3 ）: 227 ⁃ 235 .

杨荣菲 , 黄进 , 杨小平 , 等 . 粗糙度对高/低雷诺数跨声压气机性能的影响 [J]. 燃气涡轮试验与研究， 2017 , 30 （ 2 ）: 37 ⁃ 44 .

YANG Rongfei , HUANG Jin , YANG Xiaoping , et al . Effect of roughness on high/low Reynolds number transonic compressor performance [J]. Gas Turbine Experiment and Research ， 2017 , 30 （ 2 ）: 37 ⁃ 44 . （in Chinese）

SYVERUD E , BAKKEN L E . The impact of surface roughness on axial compressor performance deterioration [R]. ASME Paper 2006⁃GT⁃90004 , 2006 .

BACK S C , JEONG I C , SOHN J L , et al . Influence of surface roughness on the performance of a compressor blade in a linear cascade:experiment and modeling [R]. ASME Paper 2009⁃GT⁃59703 ， 2009 .

MARCO B , FABIO B , DANIELE S , et al . Combined experiment and numerical investigations on the roughness effects on the aerodynamic performances of LPT blades [J]. Journal of Thermal Science , 2016 , 25 （ 1 ）: 32 ⁃ 42 .

GBADEBO S A , HYNES T P , CUMPSTY N . Influence of surface roughness on three⁃dimensional separation in axial compressor [R]. ASME Paper 2004⁃GT⁃53619 ， 2004 .

LEIPOLD R , BOESE M , FOTTNER L . The Influence of technical surface roughness caused by precision forging on the flow around a highly loaded compressor cascade [J]. Journal of Turbomachinery ， 2000 , 122 （ 3 ）: 416 ⁃ 424 .

SCHREIBER H , STEINERT W , KÜSTERS B . Effects of Reynolds number and free⁃stream turbulence on boundary layer transition in a compressor cascade [J]. Journal of Turbomachinery , 2002 , 124 （ 1 ）: 1 ⁃ 9 .

BAMMERT K , WOELK G U . The influence of the blading surface roughness on the aerodynamic behavior and characteristic of an axial compressor [J]. Journal of Engineering for Gas Turbines and Power , 1980 , 102 （ 2 ）: 283 ⁃ 287 .

MORINI M , PINELLI M , SPINA P R , et al . Numerical analysis of the effects of non⁃uniform surface roughness on compressor stage performance [J]. Journal of Engineering for Gas Turbines and Power ， 2011 , 133 （ 7 ）: 072401.1 ⁃ 072401.8 .

ALDI N , MORINI M , PINELLI , M , et al . Performance evaluation of non⁃uniformly fouled axial compressor stages by means of computational fluid dynamic analyses [R]. ASME Paper 2013⁃GT⁃95580 ， 2013 .

CHEN S W , ZHANG C , SHI H , et al . Study on the impact of fouling on axial compressor stage [R]. ASME Paper 2012⁃GT⁃68041 ， 2012 .

CHEN S W , SUN S J , XU H , et al . Influence of local surface roughness of a rotor blade on performance of an axial compressor stage [R]. ASME Paper 2013⁃GT⁃94816 ， 2013 .

YANG C W , LU X G , ZHANG Y F , et al . Numerical investigation of a cantilevered compressor stator at varying clearance sizes [R]. ASME Paper 2015⁃GT⁃42124 ， 2015 .

BOESE M , FOTTNER L . Effects of riblets on the loss behavior of a highly loaded compressor cascade [R]. ASME Paper GT⁃2002⁃30438 , 2002 .

MORINI M , PINELLI M , SPINA P R , et al . Computational fluid dynamics simulation of fouling on axial compressor stages [J]. Journal of Engineering for Gas Turbines and Power , 2010 , 132 （ 7 ）: 072401.1 ⁃ 072401.10 .

SUDER K L ， CHIMA R V , STRAZISAR A J ， et al . The effect of adding roughness and thickness to a transonic axial compressor rotor [J]. Journal of Turbomachinery , 1995 , 117 （ 4 ）: 491 ⁃ 505 .

BONS J P . A review of surface roughness effects in gas turbines [J]. Journal of Turbomachinery , 2010 , 132 （ 2 ）: 021004.1 ⁃ 021004.16 .

KOCH C , SMITH L H . Loss sources and magnitudes in axial⁃flow compressors [J]. Journal of Engineering for Gas Turbines and Power , 1976 , 98 （ 3 ）: 411 ⁃ 424 .

LAUNDER B E , SPALDING D B . The numerical computation of turbulent flows [J]. Computer Methods in applied Mechanics and engineering , 1974 , 8 （ 3 ）: 266 ⁃ 289 .

ANSYS Incorporation . ANSYS CFX⁃Solver theory guide release 13 . 0 [M]. Canonsburg,PA,US : ANSYS Incorporation ,2010: 129 ⁃ 131 .

LI Z ， LIU Y . Effect of end⁃wall roughness on performance of transonic axial compressor [J]. Journal of Aerospace Engineering ， 2017 , 231 （ 7 ）: 1213 ⁃ 1224 .

FOUFLIAS D , GANNAN A , RAMSDEN K , et al . CFD predictions of cascade pressure losses due to compressor fouling [R]. ASME Paper 2009⁃GT⁃59158 , 2009 .

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