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Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction

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Abstract

Effects of inlet boundary layer suction on the vortex structure and cascade loss in a highly loaded compressor cascade were investigated experimentally. Ink-track visualization was undertaken on cascade endwall and the blade surface. Ten traverse planes from upstream to downstream of the cascade in a rectangular wind tunnel were measured by an L-shaped five-hole probe. These tested planes revealed the process of emergence, development and decline of several principal vortices as well as the corresponding additional losses. Details of ink-track visualization displaying the secondary flow behavior of boundary layer upon endwall and blade surface assist to make judgment on vortex evolution. Inspection of the vortex structure revealed that highly loaded compressor was characterized by large-scale vortices in the endwall region. After suction, these vortices are all well organized and under control. Among all of them, passage vortex is most sensitive to the variation of the inlet boundary layer, and its main function is to spread low-energy fluid rather than to produce loss. On the other hand, a wall vortex and a concentrated shedding vortex take place inside and after the cascade, respectively, and engender considerable accompanying loss as they dissipate. The effects of inlet boundary layer suction on them are correspondingly weaker. About one forth of the total loss in the baseline cascade was eliminated when boundary layer suction flow rate reaches 2.5 % of the inlet mass flow. The feasibility of simplifying the suction system is also verified through this work.

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Abbreviations

B :

Axial blade chord

b :

Blade chord

d :

Suction slot width

h :

Blade height

i :

Incidence

P :

Pressure

Re :

Reynolds number

t :

Blade pitch

U :

Inlet velocity

u :

Axial component of velocity

v :

Circumferential component of velocity

w :

Spanwise component of velocity

x :

Circumferential direction

y :

Spanwise direction

ORI:

Baseline scheme without suction slot

EW0:

Schemes with suction slot on the endwall

CSV:

Concentrated shedding vortex

CV:

Corner vortex

PV:

Passage vortex

WV:

Wall vortex

α 1P :

Inlet metal angle

α 2P :

Outlet metal angle

β :

Suction flow rate relative to inlet mass flow

β t :

Stagger angle

θ :

Blade camber angle

ρ :

Density

σ :

Chord to pitch ratio, solidity

ω :

Total pressure coefficient

Ω Z :

Axial component of vorticity

0:

Stagnation

1:

Inlet

2:

Outlet

v :

Velocity

t :

Total

m :

Overall mass-averaged

—:

Relative value

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Acknowledgments

The present study was supported by the Fundamental Research Funds for the Central Universities of China (DUT11RC(3)78), Specialized Research Fund for the Doctoral Program of Higher Education of China (No. 20112125120009) and the National Natural Science Foundation of China (No. 51206013). The authors are grateful to these supports.

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Authors and Affiliations

  1. State Key Laboratory of Structural Analysis for Industrial Equipment, School of Aeronautics and Astronautics, Dalian University of Technology, 2# Linggong Road, Ganjingzi District, Dalian, 116024, Liaoning, People’s Republic of China

    Shuang Guo & Chuijie Wu

  2. Marine Engineering College, Dalian Maritime University, Dalian, People’s Republic of China

    Huawei Lu

  3. School of Energy Science and Engineering, Harbin Institute of Technology, Harbin, People’s Republic of China

    Fu Chen

Authors
  1. Shuang Guo
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  2. Huawei Lu
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  3. Fu Chen
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  4. Chuijie Wu
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Correspondence to Shuang Guo.

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Guo, S., Lu, H., Chen, F. et al. Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction. Exp Fluids 54, 1570 (2013). https://doi.org/10.1007/s00348-013-1570-y

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  • DOI: https://doi.org/10.1007/s00348-013-1570-y

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