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Multiphase Flows

Influence of the Blade Number on Inducer Cavitating Behavior

[+] Author and Article Information
O. Coutier-Delgosha

Arts et Metiers ParisTech/LML Laboratory, 8 Boulevard Louis XIV, 59046 Lille Cedex, Franceolivier.coutier@ensam.eu

G. Caignaert

Arts et Metiers ParisTech/LML Laboratory, 8 Boulevard Louis XIV, 59046 Lille Cedex, Franceguy.caignaert@ensam.eu

G. Bois

Arts et Metiers ParisTech/LML Laboratory, 8 Boulevard Louis XIV, 59046 Lille Cedex, Francegerard.bois@ensam.eu

J.-B. Leroux1

Arts et Metiers ParisTech/LML Laboratory, 8 Boulevard Louis XIV, 59046 Lille Cedex, Francejean-baptiste.leroux@ensieta.fr

1

Present address: ENSIETA - Laboratoire MSN, 2 Rue François Verny, 29806 Brest Cedex 9, France.

J. Fluids Eng 134(8), 081304 (Aug 09, 2012) (11 pages) doi:10.1115/1.4006693 History: Received February 26, 2010; Revised August 26, 2011; Published August 09, 2012; Online August 09, 2012

Effects of the blade number on the performance of a rocket engine turbopump inducer are investigated in the present paper. For that purpose, two inducers characterized by three blades and five blades, respectively, were manufactured and tested experimentally. The two inducers were designed on the basis of identical design flow rate and identical pressure elevation at nominal flow rate. The first part of the study focuses on the steady behavior of the inducers in cavitating conditions: evolutions of performance, torque, mass flow rate, and amplitude of radial forces on the shaft according to the inlet pressure are considered. Several flow rates and rotation speeds are investigated. Significant differences between the inducers are obtained concerning the critical cavitation number, the amplitude of the radial forces, and the organization of cavitation in the machinery. Cavitation instabilities are investigated in the second part of the study. Various flow patterns are detected according to the mass flow rate and the cavitation number.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Rocket engine turbopump inducer

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Figure 2

Sketches of cavitation patterns and performance evolution as the cavitation number decreases in a four-blade inducer (from Joussellin [3])

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Figure 3

General view of the LML large test facility

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Figure 4

Scheme of the inducer test section including the acquisition equipment

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Figure 5

(a) Head coefficient drop charts and (b) torque coefficient drop charts (IND3, Nref , Qn )

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Figure 6

Head drop charts for rotation speeds Nref , 0.8 Nref , and 1.2 Nref (IND3, Qn , type #1 and #2 experiments)

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Figure 7

Flow visualizations for (a) τ+  = 0.6 and (b) τ+  = 0.25 (0.6 Nref , Qn )

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Figure 8

Torque coefficient drop for IND3 and IND5 (Nref , Qn , type #1 experiments)

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Figure 9

Torque coefficient drop for IND3 and IND5 (Nref , Qn , type #2 experiments)

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Figure 10

Flow rate coefficient drop for IND3 and IND5 (Nref , Qn , type #2 experiments)

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Figure 11

Influence of the rotation speed on the value of τ corresponding to (a) 3% Ψ+ drop and (b) 3% χ+ drop (Qn , type #2 experiments)

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Figure 12

Flow visualizations for (a) 3% ψ+ drop and (b) 3% χ+ drop (0.6 Nref , Qn )

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Figure 13

Evolution of τ+ c according to the mass flow rate for (a) 3%, (b) 10%, and (c) 20% ψ+ drop

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Figure 14

Evolution of τ+ c according to the mass flow rate for (a) 3% and (b) 10% χ+ drop

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Figure 15

Influence of (a) the rotation speed and (b) the mass flow rate on the maximum value of the RMS fluctuation of Fy + (type #2 experiment)

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Figure 16

Spectral analysis of (a) Fy and (b) P′2 (IND3, Qn , Nref )

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Figure 17

Fy and Fz fluctuations during the super-synchronous rotating cavitation (IND3, Nref , Qn , τ+ ≈ 0.25, low-pass filter with cutoff frequency 400 Hz)

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Figure 18

Front views of the inducer during super-synchronous rotating cavitation (IND3, 0.6 Nref , Qn )

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Figure 19

P′1 and P′2 fluctuations during the super-synchronous rotating cavitation (IND3, Nref , Qn , τ+ ≈ 0.25, low-pass filter with cutoff frequency 200 Hz)

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Figure 20

Fy and Fz fluctuations during the stable nonsymmetrical regime (IND3, Nref , Qn , τ+ ≈ 0.17, low-pass filter with cutoff frequency 400 Hz)

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Figure 21

P′1 and P′2 fluctuations during the stable nonsymmetrical regime (IND3, Nref , Qn , τ+ ≈ 0.17, low-pass filter with cutoff frequency 200 Hz)

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Figure 22

Cartography of the frequencies detected for (a) IND3 and (b) IND5. Indicated frequencies are related to the rotating frame.

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