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TECHNICAL PAPERS

Numerical Model to Predict Unsteady Cavitating Flow Behavior in Inducer Blade Cascades

[+] Author and Article Information
R. Fortes-Patella1

Laboratoire des Ecoulements Géophysiques et Industriels, LEGI–INPG, BP 53, 38041 Grenoble cedex 9, Francefortes@hmg.inpg.fr

O. Coutier-Delgosha2

Laboratoire des Ecoulements Géophysiques et Industriels, LEGI–INPG, BP 53, 38041 Grenoble cedex 9, France

J. Perrin

Laboratoire des Ecoulements Géophysiques et Industriels, LEGI–INPG, BP 53, 38041 Grenoble cedex 9, France

J. L. Reboud3

Laboratoire des Ecoulements Géophysiques et Industriels, LEGI–INPG, BP 53, 38041 Grenoble cedex 9, France

1

Corresponding author.

2

Now at LML/ENSAM Lille.

3

Now at CNRS-LEMD, University of Grenoble, France.

J. Fluids Eng 129(2), 128-135 (May 23, 2006) (8 pages) doi:10.1115/1.2409320 History: Received November 25, 2003; Revised May 23, 2006

The cavitation behavior of a four-blade rocket engine turbopump inducer is simulated. A two-dimensional numerical model of unsteady cavitation was applied to a blade cascade drawn from an inducer geometry. The physical model is based on a homogeneous approach of cavitation, coupled with a barotropic state law for the liquid/vapor mixture. The numerical resolution uses a pressure-correction method derived from the SIMPLE algorithm and a finite volume discretization. Unsteady behavior of sheet cavities attached to the blade suction side depends on the flow rate and cavitation number. Two different unstable configurations of cavitation are identified. The mechanisms that are responsible for these unstable behaviors are discussed, and the stress fluctuations induced on the blade by cavitation instabilities are estimated.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 16

Axial and transverse forces on the blades (σ=0.625 and Q=Qn)

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Figure 17

Performance charts at several mass flow rates

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Figure 1

Experimental performance chart for a H2 turbopump inducer (tests in cold water) (1)

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Figure 2

Sketches of cavitation patterns for various cavitation parameters and their correspondence to the performance curve (1)

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Figure 4

Blade cut in the plane (Rc.θ,Z)

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Figure 5

Curvilinear, orthogonal mesh of a single channel (general view and zoom at the blade leading edge)

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Figure 6

Comparison between the performance charts obtained with four-blade computations (—•—) and with single blade computations (———) at nominal flow rate

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Figure 7

Cavitation development for σ=0.8 and Q=Qn: (a) Density fields: white corresponds to pure liquid, and black to pure vapor (scale ratio x∕y≈10). (b) Time evolution of the cavity in the first channel. The time is reported in abscissa, and the Z position on the blade is graduated in ordinate. The colors (shading) represent the density values. At a given point in time and position, the color (shading) indicates the minimum density in the corresponding cross section of the channel.

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Figure 8

Time evolution of the nondimension mass flow rate in the four channels (σ=0.7 and Q=Qn)

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Figure 9

Time evolution of the sheets of cavitation (110<T∕Tref<135)

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Figure 10

Deviation of velocities due to high void ratio (T=110Tref)

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Figure 11

Spectral analysis (σ=0.7, Q=Qn): (a) Mass flow rate downstream from the blades, in the rotating frame and (b) static pressure far upstream from the blades, in the absolute frame (results concerning a calculation time of about 30 rotation periods of the inducer)

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Figure 12

Spectral analysis (σ=0.7, Q=Qn): (a) Total pressure near to the leading edge, in the absolute frame and (b) total pressure far upstream from the blades, in the absolute frame (results concerning a calculation time of ∼30 rotation periods of the inducer)

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Figure 13

Time evolution of the non dimension mass flow rates in the four channels (σ=0.625, Q=Qn)

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Figure 14

Spectral analysis (σ=0.625, Q=Qn): (a) Mass flow rate downstream from the blades, in the rotating frame and (b) static pressure far upstream from the blades, in the absolute frame (results concerning a calculation time of ∼30 rotation periods of the inducer)

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Figure 15

Time distribution of the axial and transverse forces on the blades (σ=0.7 and Q=Qn)

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