A Reduced Order Model for Preliminary Design and Performance Prediction of Tapered Inducers: Comparison with Numerical Simulations

d’Agostino, Luca; Torre, Lucio; Pasini, Angelo; Baccarella, Damiano; Cervone, Angelo; Milani, Andrea

doi:10.2514/6.2008-5119

Cited by 27 publications

(22 citation statements)

References 13 publications

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“…As anticipated earlier, the DAPAMITO inducers have been designed based on the reduced-order model and procedure [30,31]. They are high-head mixed-flow inducers with tapered hubs and variable pitch.…”

Section: B Test Articlementioning

confidence: 99%

“…Figure 6 shows the noncavitating experimental curves in terms of the static head coefficient p= 2 r 2 T as a function of the flow coefficient Q=r 3 T , obtained by tests conducted at a water temperature of 19.2 C, and the comparison with the predictions provided by the analytical model used for designing the inducer [21,30,31,33]. Experimental data for c % 6:8% are presented for three different values of the rotating speed (1500, 2000, and 2500 rpm), whereas those for c % 2:7% are presented only at 2500 rpm.…”

Section: A Noncavitating and Cavitating Performancementioning

confidence: 99%

“…The tests have been carried out on the DAPAMITO3 inducer: a three-bladed axial pump designed and manufactured using a simplified analytical model for the prediction of geometry and noncavitating performance of typical space rocket inducers [30,31]. A series of tests have been conducted at high and moderate values of the tip clearance-to-mean blade height ratio: 6.8 and 2.7%, respectively.…”

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confidence: 99%

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Effect of Tip Clearance on the Performance of a Three-Bladed Axial Inducer

Torre¹,

Pasini²,

Cervone³

et al. 2011

Journal of Propulsion and Power

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This paper illustrates the results of an experimental campaign conducted in the Cavitating Pump Rotordynamic Test Facility. Tests have been carried out at two values of the blade tip clearance on the three-bladed DAPAMITO3 inducer, designed by means of a reduced-order model, with geometry and noncavitating performance representative of typical space rocket inducers. Different cavitating behaviors have been observed at different values of the blade tip clearance, particularly near breakdown conditions. The intensity of pressure oscillations tends to decrease as the tip blade clearance increases, and cavitation-induced azimuthal flow instabilities appear to be more sensitive to changes of the blade tip clearance than axial flow instabilities. Finally, the presence of backflow seems to have a stabilizing effect on rotating cavitation instabilities. Nomenclature c % = tip clearance/mean blade height ratio c % =h m f1; 2; . . . = name of instability h m = mean blade height, m n = number of lobes p in = inlet static pressure, Pa p V = vapor pressure, Pa Q = volumetric flow rate, m 3 =s Re = Reynolds number; 2r 2 T = r T = inducer tip radius, m b = blade angle evaluated with respect to the azimuthal direction, rad xy = coherence function p = static pressure rise across inducer, Pa = angular spacing between transducers, rad = tip clearance, m = kinematic viscosity, m 2 =s = liquid density, kg=m 3 = cavitation number; p 1 p V =0:5 2 r 2 T = flow coefficient; Q=r 3 T D = design flow coefficient ' = phase of cross spectrum, rad = static head coefficient; p= 2 r 2 T = inducer rotational speed, rad=s

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Section: B Test Articlementioning

confidence: 99%

Section: A Noncavitating and Cavitating Performancementioning

confidence: 99%

mentioning

confidence: 99%

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Effect of Tip Clearance on the Performance of a Three-Bladed Axial Inducer

Torre¹,

Pasini²,

Cervone³

et al. 2011

Journal of Propulsion and Power

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“…The DAPROT3 high-head, tapered-hub, three-bladed inducer, is also manufactured in 7075-T6 aluminum alloy. The test articles, whose relevant geometrical and operational data are reported in Table 2, have been designed by means of two reduced order model developed at ALTA and described in [15,16] (inducer) and in [17,18,19] (centrifugal pump). The two machines operate at the same design flowrate allowing for coupling in the resulting VAMPDAP configuration.…”

Section: Test Articlesmentioning

confidence: 99%

Inducer and Centrifugal Pump Contributions to the Rotordynamic Fluid Forces Acting on a Space Turbopump

Pace¹,

Valentini²,

Pasini

et al. 2017

Journal of Fluids Engineering

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The fluid induced rotordynamic forces acting on a whirling space turbopump composed by an inducer and a radial impeller have been compared to the same forces measured on each single component of the turbomachine (i.e. on the inducer and on the radial impeller). The experimental campaign has been carried out in cold water at design and off-design conditions (80%, 100% and 120% of the design flow rate) both in non-cavitating and cavitating regimes. The paper illustrates the different trends of the rotordynamic forces on the axial and radial pumps and highlights their contributions on the overall turbomachine. At positive whirl ratios, the behavior of the inducer is dominant while, at negative ones, both the pumps show the same trends in such a way that the overall behavior is roughly the sum of each single component.

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“…The main features of the model have been extensively presented in two previous papers (d'Agostino et al, [12], [13]), and can be summarized as follows. Under the assumptions of incompressible, inviscid and irrotational flow, the model approximates the 3D flow field inside the blade channels by superposing a 2D cross-sectional vorticity correction to a fully-guided axisymmetric flow with radially uniform axial velocity.…”

Section: Introductionmentioning

confidence: 99%

Cavitation and Flow Instabilities in a 4-Bladed Axial Inducer Designed by Means of a Reduced Order Analytical Model

Cervone¹,

Torre²,

Pasini³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The present paper illustrates the main results of an experimental campaign conducted using the CPRTF (Cavitating Pump Rotordynamic Test Facility) at Alta S.p.A. The tests were carried out on the DAPAMITO inducer, a three-bladed axial pump designed and manufactured by Alta S.p.A. using a simplified analytical model for the prediction of geometry and noncavitating performance of typical space rocket inducers. The transparent inlet section of the facility was instrumented with several piezoelectric pressure transducers located at three axial stations: inducer inlet, outlet and the middle of the axial chord of the blades. At each axial station at least two transducers were mounted with given angular spacing in order to cross-correlate their signals for amplitude, phase and coherence analysis. However, probably because of the high value of the blade tip clearance, very few flow instabilities have been detected on the inducer, including: steady asymmetric cavitation caused by the different extension of the cavitating regions on the blades; cavitation surge at a frequency equal to 0.16 times the inducer rotational frequency; a higher-order axial phenomenon at 7.2 times the rotational frequency.

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A Reduced Order Model for Preliminary Design and Performance Prediction of Tapered Inducers: Comparison with Numerical Simulations

Cited by 27 publications

References 13 publications

Effect of Tip Clearance on the Performance of a Three-Bladed Axial Inducer

Effect of Tip Clearance on the Performance of a Three-Bladed Axial Inducer

Inducer and Centrifugal Pump Contributions to the Rotordynamic Fluid Forces Acting on a Space Turbopump

Cavitation and Flow Instabilities in a 4-Bladed Axial Inducer Designed by Means of a Reduced Order Analytical Model

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