Abstract
An extensive numerical investigation is conducted to characterize the flow separation control in a transonic compressor cascade with a porous bleed. The bleed holes are arranged on the suction surface in a single row, two staggered rows and three staggered rows. For each bleed scheme, five bleed pressure ratios are examined at an inlet Mach number of 1.0. The results indicate that the aerodynamic performance of the cascade is significantly improved by the porous bleed. For the single-row scheme, the maximum reduction in total pressure losses is 57%. For the two-staggered-row and three-staggered-row schemes, there is an optimal bleed pressure ratio of 1.0, and the maximum reductions in total pressure loss are 68% and 75%, respectively. The low loss in the cascade is due to the well-controlled boundary layer. The new local supersonic region created by the bleed hole is the key reason for the improved boundary layer. The vortex induced by side bleeding provides another mechanism for delaying flow separation. Increasing the bleed holes could create multiple local supersonic regions, which reduce the range of the adverse pressure gradient that the boundary layer needs to withstand. This is the reason why cascades with more bleed holes perform better.
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Abbreviations
- AVDR:
-
axial velocity density ratio
- b :
-
length of plenum/mm
- BR:
-
mb/m1
- C :
-
blade chord
- c :
-
width of plenum/mm
- d :
-
suction hole diameter/mm
- h :
-
spanwise height of blade/mm
- L :
-
axial length/mm
- l :
-
suction hole length/mm
- m 1 :
-
inlet mass flow rate/kg·s−1
- m b :
-
bleeding mass flow rate/kg·s−1
- Ma :
-
Mach number
- P b :
-
bleed pressure/Pa
- P s :
-
static pressure/Pa
- P t :
-
total pressure/Pa
- T t :
-
total temperature/K
- t :
-
vane pitch/mm
- V :
-
local velocity/m·s−1
- Vin:
-
inlet flow velocity/m·s−1
- V N :
-
normal velocity/m·s−1
- V T :
-
tangential velocity/m·s−1
- X, Y, Z :
-
cartesian coordinates/mm
- y + :
-
non-dimensional grid spacing at the wall
- β :
-
angle/(°)
- θ :
-
flow turning/(°)
- ω :
-
total pressure loss coefficient
- ρ :
-
air density/kg·m−3
- 1:
-
inlet
- 2:
-
outlet
References
Schulz H.D., Three-dimensional separated flow field in the endwall region of an annular compressor cascade in the presence of rotor-stator interaction: Part 2–unsteady flow and pressure field. Journal of Turbomachinery, 1990, 112(4): 679–690.
Gbadebo S.A., Cumpsty N.A., Hynes T.P., Three-dimensional separations in axial compressors. Journal of Turbomachinery, 2005, 127(2): 457–469.
Zander V., Dobriloff C., Lumpe M., et al., Wall shear stress measurements on a highly loaded compressor cascade. Journal of Turbomachinery, 2011, 135(1): 1–8.
Beselt C., Eck M., Peitsch D., Three-dimensional flow field in a highly loaded compressor cascade. Journal of Turbomachinery, 2014, 136(10): V02DT44A018.
Kerrebrock J.L., Reinjen D.P., Ziminsky W.S., et al., Aspirated compressors. ASME International Gas Turbine & Aeroengine Congress & Exhibition 1997, Orlando, USA, Paper No. 97-GT-525.
Kerrebrock J.L., Drela M., Merchant A.A., et al., Family of designs for aspirated compressors. ASME International Gas Turbine and Aeroengine Congress and Exhibition 1998, Stockholm, Sweden, Paper No. 98-GT-196.
Kerrebrock J.L., The prospects for aspirated compressors. Fluids Conference and Exhibit, 1998, Paper No. AIAA 2000-2472.
Power B., Xu L., Wellborn S., Numerical and experimental findings of a highly-loaded aspirated cascade. ASME Turbo Expo Turbine Technical Conference and Exposition 2014, Düsseldorf, Germany, Paper No. GT2014-27098.
Zhou X., Zhao Q., Xiang X., et al., Investigation of groove casing treatment in a transonic compressor at different speeds with control volume method. Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, 2016, 230(G13): 191–197.
Zhou X., Zhao Q., Cui W., et al., Investigation on axial effect of slot casing treatment in a transonic compressor. Applied Thermal Engineering, 2017, 126: 53–69.
Dinh C.T., Vu D.Q., Kim K.Y., Effects of rotor-bleeding airflow on aerodynamic and structural performances of a single-stage transonic axial compressor. International Journal of Aeronautical and Space Sciences, 2019, 21: 599–611.
Zhao B., Li S., Li Q., et al., The impact of bleeding on compressor stator corner separation. ASME-JSME-KSME 2011, Shizuoka, Japan, Paper No. AJK2011-22001.
Borra H.K., Alone D.B., Stall margin improvement of a single stage transonic axial flow compressor using naturally aspirated slots. Proceedings of the ASME Gas Turbine India Conference 2015, Hyderabad, India, Paper No. GTINDIA2015-1211.
Merchant A., Kerrebrock J., Epstein A., Compressors with aspirated flow control and counter-rotation. 2nd AIAA Flow Control Conference 2004, Oregon, USA, Paper No. AIAA 2004-2514.
Schuler B.J., Kerrebrock J.L., Merchant A., Experimental investigation of a transonic aspirated compressor. Journal of Turbomachinery, 2005, 127(1): 43–51.
Cao Z., Gao X., Zhang T., et al., Flow mechanism and aspiration strategies in an ultra-highly loaded supersonic compressor cascade. Aerospace Science and Technology, 2020, 104(1): 105989.
Wang Y.G., Guo R.H., Zhao L.B., et al., Numerical investigation on the effects of re-organized shock waves on the flow separation for a highly-loaded transonic compressor cascade. Journal of Thermal Science, 2012, 21(1): 13–20.
Wang Y.G., Rao A.G., Eitelberg G., Study of shock wave control by suction & blowing on a highly-loaded transonic compressor cascade. International Journal of Turbo and Jet Engines, 2013, 30(1): 79–90.
Chen S.W., Sun S.J., Hao X., et al., Experimental study of the impact of hole-type suction on the flow characteristics in a high-load compressor cascade with a clearance. Experimental Thermal & Fluid Science, 2013, 51(1): 220–226.
Zhang H.X., Chen S.W., Meng Q.H., et al., Flow separation control using unsteady pulsed suction through endwall bleeding holes in a highly loaded compressor cascade. Aerospace Science and Technology, 2018, 72(1): 455–464.
Ding J., Chen S., Hao X., et al., Control of flow separations in compressor cascade by boundary layer suction holes in suction surface. ASME Turbo Expo: Turbine Technical Conference & Exposition 2013, Texas, USA, Paper No. GT2013-94723.
Chen S.W., Gong Y., Li W.H., et al., Numerical study of the air bleeding caused non-uniformity in axial compressor. Journal of Thermal Science, 2020, 29(1): 219–231.
Hamed A., Morell A., Bellamkonda G., Three-dimensional simulations of bleed-hole rows/shock-wave/turbulent boundary-layer interactions. AIAA Aerospace Sciences Meeting Including the New Horizons Forum & Aerospace Exposition 2012, Tennessee, USA, Paper No. AIAA 2012-0840.
Shih T., Control of shock-wave/bound-layer interactions by bleed. International Journal of Fluid Machinery & Systems, 2008, 1(1): 24–32.
Rimlinger M.J., Shih I.P., Chyu W.J., Shock-wave/boundary-layer interactions with bleed through rows of holes. Journal of Propulsion & Power, 1996, 12(2): 217–224.
Hu Y.J., Wang S.T., Zhang L.X., et al., Aerodynamic design of a highly loaded supersonic aspirated axial flow compressor stage. Proceedings of the Institution of Mechanical Engineers Part A Journal of Power and Energy, 2014, 228(3): 241–254.
Dunker R.J., Hungenberg H.G., Transonic axial compressor using laser anemometry. AIAA Journal, 1980, 18(8): 973–979.
Li B., Mu G., Luo L., et al., Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2023: 09576509231205346
Davis D.O., Willis B.P., Hingst W.R., Flowfield measurements in a slot-bled oblique shock wave and turbulent boundary-layer interaction. Aerospace Sciences Meeting and Exhibit 1998, Washington, USA, Paper No. AIAA 95-0032.
Koo B., Kang Y.D., Control of synthetic hairpin vortices in laminar boundary layer for skin-friction reduction. Journal of Marine Science and Engineering, 2020, 8(1): 1–14.
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The author acknowledges the financial support provided by the National Science and Technology Major Project (2017-II-0007-0021).
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Li, B., Zhou, X., Luo, L. et al. Effects of Number of Bleed Holes on Shock-Wave/Boundary-Layer Interactions in a Transonic Compressor Stator. J. Therm. Sci. 33, 611–624 (2024). https://doi.org/10.1007/s11630-024-1908-1
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DOI: https://doi.org/10.1007/s11630-024-1908-1