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Research Papers

Large Eddy Simulation for a Deep Surge Cycle in a High-Speed Centrifugal Compressor With Vaned Diffuser

[+] Author and Article Information
Ibrahim Shahin

Mechanical and Industrial Engineering Department,
College of Engineering,
Qatar University,
Doha 2713, Qatar
Mechanical Engineering Department,
Shoubra Faculty of Engineering,
Benha University,
Benha, Egypt
e-mails: Ibrahimshahin@qu.edu.qa;
Ibrahim.shahin@feng.bu.edu.eg

Mohamed Gadala

Mechanical Engineering Department,
UBC-University of British Columbia,
Vancouver, BC V6T 1Z4, Canada
e-mail: gadala@mail.ubc.ca

Mohamed Alqaradawi

Mechanical and Industrial Engineering Department,
College of Engineering,
Qatar University,
Doha 2713, Qatar
e-mail: myq@qu.edu.qa

Osama Badr

Mechanical Engineering Department,
The British University in Egypt,
Alshorouk, New Cairo, Egypt
e-mail: osama.badr@Bue.edu.eg

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 20, 2014; final manuscript received June 2, 2015; published online June 23, 2015. Assoc. Editor: Ricardo F. Martinez-Botas.

J. Turbomach 137(10), 101007 (Jun 23, 2015) (15 pages) Paper No: TURBO-14-1249; doi: 10.1115/1.4030790 History: Received September 20, 2014

This paper presents a computational study for a high-speed centrifugal compressor stage with a design pressure ratio equal to 4, the stage consisting of a splittered unshrouded impeller and a wedged vaned diffuser. The aim of this paper is to investigate numerically the modifications of the flow structure during a surge cycle. The investigations are based on the results of unsteady three-dimensional, compressible flow simulations, using large eddy simulation (LES) model. Instantaneous and mean flow field analyses are presented in the impeller inducer and in the vaned diffuser region through one surge cycle time intervals. The computational data compare favorably with the measured data, from the literature, for the same compressor and operational point. The surge event phases are well detected inside the impeller and diffuser. The time-averaged loading on the impeller main blade is maximum near the trialing edge and near the tip. The amplitude of the unsteady pressure fluctuation is maximum for the flow reversal condition and reaches values up to 70% of the dynamic pressure. The diffuser vane exhibits high-pressure fluctuation from the vane leading edge to 50% of the chord length. High-pressure fluctuation is detected during the forward flow recovery condition as a result of the shock wave that moves toward the diffuser outlet.

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References

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Figures

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Fig. 1

The geometry of simulated parts: (a) 120 deg sector, (b) full domain, (c) enlarged view, and (d) view with casing removal

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Fig. 2

Computational domain grid: (a) with casing removal and (b) without casing removal

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Fig. 3

Mesh details at different locations inside the domain and boundary conditions

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Fig. 4

Performance parameters at design flow rate with different number of computational nodes

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Fig. 5

Pressure ratio of the compressor stage for the present CFD results “URANS and LES models” and experimental results [11]

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Fig. 6

Comparison of absolute velocities at 95% span plan at off design point: (a) URANS and (b) LES model

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Fig. 7

Comparison of velocities measured [12] “right” and present simulation “left” in the vaned diffuser at different flow conditions during surge

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Fig. 8

Area weighted average for the mass flow rate at diffuser outlet

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Fig. 9

Area weighted average for the inst. static pressure at diffuser outlet plane and the mass flow rate at impeller with the flow time

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Fig. 10

Dynamic pressure with the flow time at midspan point “1.08R2” for design flow rate

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Fig. 11

Dynamic pressure with the flow time at midspan point “1.08R2” for surge flow rate

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Fig. 12

The FFT analysis for the pressure signal at surge flow rate

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Fig. 13

Instantaneous static pressure in Pa at 95% span plane

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Fig. 14

Dimensionless instantaneous velocity “V/U2” at 95% span plane

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Fig. 16

Isosurface for instantaneous velocity in the diffuser

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Fig. 17

Vorticity magnitude and relative velocity prior to surge

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Fig. 18

Dimensionless instantaneous axial velocity “Vaxial/U2” at 95% span plane

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Fig. 19

Streamlines and velocity vectors in impeller inducer “95% span plane” at different surge phases

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Fig. 20

Impeller blade mean static pressure loading at: (a) 50% span and (b) 95% span

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Fig. 21

Impeller blade RMS static pressure loading at: (a) 50% span and (b) 95% span

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Fig. 22

Diffuser vane mean static pressure loading at: (a) 50% span and (b) 95% span

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Fig. 23

Diffuser vane RMS static pressure loading at: (a) 50% span and (b) 95% span

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