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Research Papers: Multiphase Flows

Thermodynamic Effect on a Cavitating Inducer in Liquid Hydrogen

[+] Author and Article Information
Eric Goncalvès1

LEGI, Grenoble INP, Grenoble 38041, Franceeric.goncalves@legi.grenoble-inp.fr

Regiane Fortes Patella

LEGI, Grenoble INP, Grenoble 38041, France

Julien Rolland, Benoit Pouffary

 CNES, Evry 91000, France

Guillaume Challier

 Snecma, Vernon 27200, France

1

Corresponding author. Present address: LEGI, Domaine Universitaire, 38400 Saint Martin d’Heres, France.

J. Fluids Eng 132(11), 111305 (Nov 18, 2010) (7 pages) doi:10.1115/1.4002886 History: Received October 13, 2009; Revised September 16, 2010; Published November 18, 2010; Online November 18, 2010

This study was led in collaboration with the French Space Agency (CNES) and the Rocket Engine Division of Snecma. The main aims were the simulations and the analyses of cavitating flows in the rocket engine turbopump inducers, where the operating fluids are LH2 and LOx under cryogenic conditions. A ρ(P,T) state law modeling the cavitation phenomenon was integrated by the laboratory LEGI in the commercial computational fluid dynamics (CFD) code FINE/TURBO ™ , developed by Numeca International. Various 3D numerical results are given for an inducer geometry and comparisons are made with experimental data (head drop curves) obtained by NASA.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

View of the inducer

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Figure 2

View of the blade leading edge

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Figure 3

View of the mesh

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Figure 4

Head drop chart, computations versus experiments

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Figure 5

Contours of void ratio: α=0.1, ϕ=0.108, and Tref=23 K

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Figure 6

Meridian view, cutting plane

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Figure 7

Void ratio on a midspan cut, blade-to-blade view, ϕ=0.108 and Tref=23 K

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Figure 8

Temperature on a midspan cut, blade-to-blade view, ϕ=0.108 and Tref=23 K

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Figure 9

Void ratio on a near-shroud cut, blade-to-blade view, ϕ=0.108 and Tref=23 K

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Figure 10

Void ratio on a near-shroud cut, blade-to-blade view, ϕ=0.098 and Tref=19 K

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Figure 11

Temperature on a near-shroud cut, blade-to-blade view, ϕ=0.108 and Tref=23 K

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Figure 12

Wall temperature on suction side, ϕ=0.108 and Tref=23 K

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Figure 13

Wall temperature on suction side in cavitating conditions

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Figure 14

Wall temperature on pressure side in cavitating conditions

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Figure 15

Wall temperature on suction side, ϕ=0.098 and Tref=19 K

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Figure 16

Wall heat transfer on suction side, ϕ=0.108 and Tref=23 K

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Figure 17

View of meshes: coarse (left) and fine (right)

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Figure 18

Wall temperature on suction side, ϕ=0.103 and Tref=22 K fine meshes

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