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Effects of Rotor-Bleeding Airflow on Aerodynamic and Structural Performances of a Single-Stage Transonic Axial Compressor

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Abstract

This paper presents the effects of airflow bleed from the rotor shroud surface between leading and trailing edges on aerodynamic and structural performances of a single-stage transonic axial compressor, NASA stage 37, using three-dimensional Reynolds-averaged Navier–Stokes equations with the k–ε turbulence model. A small airflow mass flow rate is bleed throughout a rotor-bleeding ejector which designed by seven parameters: bleeding angle (°) and ejection angles (°), ejection depth (D), bleeding thickness (H), bleeding position from rotor leading edge (L) in flow direction, bleeding ejection curvature (R), and bleeding width contacted on rotor shroud surface (W). The numerical results for aerodynamic performance: total pressure ratio, adiabatic efficiency, and stall margin of a transonic axial compressor were validated with a smooth casing experimental data. A parametric study of seven design parameters of rotor-bleeding ejector above combined with a small ejection mass flow rate in a single-stage transonic axial compressor for aerodynamic and structural performances was performed. The numerical results show that all aerodynamic performance increases with bleeding airflow from rotor shroud surface, the total deformation on rotor tip leading edge in spanwise direction reduces with a very small increasing in Von-Mises stress in a reference-bleeding airflow as compared to the results of smooth casing.

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Abbreviations

C :

Chord length of blade tip (mm)

D :

Depth of rotor-bleeding ejector at ejection port (mm)

H :

Bleeding thickness of mechanical support (mm)

L :

Distance from rotor-bleeding ejector and rotor leading edge (mm)

R :

Bleeding radii curvature of rotor-bleeding ejector (mm)

\( \dot{m} \) :

Mass flow rate (kg/s)

\( \dot{m}_{\text{B}} \) :

Mass flow rate of rotor-bleeding ejector at ejection port (kg/s)

\( \dot{m}_{\text{max} } \) :

Mass flow rate at choking condition (kg/s)

\( \dot{m}_{\text{peak}} \) :

Mass flow rate at peak efficiency condition (kg/s)

\( \dot{m}_{\text{stall}} \) :

Mass flow rate at near-stall condition (kg/s)

\( \dot{m}_{\text{SC}} \) :

Mass flow rate at choking condition of smooth casing (kg/s)

\( P_{\text{t}} \) :

Total pressure (Pa)

\( {\text{PR}}_{\text{peak}} \) :

Total pressure ratio at peak adiabatic efficiency condition (Pa)

\( {\text{PR}}_{\text{stall}} \) :

Total pressure ratio at near-stall condition (Pa)

\( T_{\text{t}} \) :

Total temperature (°C)

W :

Bleeding width (mm)

α :

Coverage angle of rotor-bleeding ejector (°)

β :

Ejection angle of rotor-bleeding ejector (°)

γ:

Specific heat ratio

η :

Adiabatic efficiency (%)

CFD:

Computational fluid dynamics

EFF:

Adiabatic efficiency (%)

PR:

Total pressure ratio

RANS:

Reynolds-averaged Navier–Stokes

SC:

Smooth casing

SM:

Stall margin (%)

SRE:

Stable range extension (%)

max:

Choking mass flow point

peak:

Peak adiabatic efficiency point

stall:

Near-stall point

bleeding:

Air-bleeding case

in:

Inlet

out:

Outlet

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Acknowledgements

This work is supported by the Vietnam National Foundation for Science and Technology Development under Grant no. 107.03-2018.20 and Vietnamese Government under Grant no. DTDL. CN-54/16.

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Authors and Affiliations

  1. Department of Aeronautical and Space Engineering, Hanoi University of Science and Technology, 1 Dai Co Viet Street, Hai Ba Trung District, Hanoi, 100000, Vietnam

    Cong-Truong Dinh & Dinh-Quy Vu

  2. Department of Mechanical Engineering, Inha University, 100 Inha-Ro, Nam-Gu, Inchon, 22212, Republic of Korea

    Kwang-Yong Kim

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Correspondence to Cong-Truong Dinh.

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Dinh, CT., Vu, DQ. & Kim, KY. Effects of Rotor-Bleeding Airflow on Aerodynamic and Structural Performances of a Single-Stage Transonic Axial Compressor. Int. J. Aeronaut. Space Sci. 21, 599–611 (2020). https://doi.org/10.1007/s42405-019-00239-5

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  • DOI: https://doi.org/10.1007/s42405-019-00239-5

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