Effect of Tip Clearance on the Cavitation Performance of a Turbopump Inducer

Hong, Soon-Sam; Kim, Jin-Sun; Choi, Changho; Kim, Jinhan

doi:10.2514/1.11982

Cited by 29 publications

(14 citation statements)

References 5 publications

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“…The pump under investigation in this study has a specific speed of 0.278 (760 US units of gal/min, ft, r/min) and its rotating part is composed of a three-bladed axial flow inducer (inlet tip blade angle 10.4 , outlet mean blade angle 17 , and tip solidity 2.6) and a seven-bladed centrifugal flow shrouded impeller with inlet mean blade angle 19 . The inducer and the impeller are shown in Figure 2.…”

Section: Test Facilitiesmentioning

confidence: 99%

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Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Hong

Kim

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part C:

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A hydraulic performance test is conducted for a fuel pump of a liquid rocket engine turbopump. The pump driven by an electric motor is tested in a water environment. Experimental results indicate that the inducer has a negligible effect on the head and efficiency of the pump but a significant effect on the cavitation performance. Additionally, an autonomous inducer test is carried out to investigate the effect of the inducer on the pump performance in more detail, and it is found out that the pump reaches a critical cavitation point when the inducer head is dropped by 55%. A reduction of required net positive suction head of the centrifugal pump by attachment of an inducer is also calculated considering the flow interference between the inducer and the centrifugal impeller, and it is found that the calculation shows a reasonable agreement with the test.

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Section: Test Facilitiesmentioning

confidence: 99%

“…Hydraulic and cavitation tests of the inducer are carried out at an inducer test facility, 17,18 which has a structure similar to that of the pump performance test facility. The working fluid is water at room temperature.…”

Section: Inducer Performance Test Facilitymentioning

confidence: 99%

Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Hong

Kim

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…The number of inducer blades affects the cavitation instability. RC is not observed at two bladed inducers, 4,5) but is observed at many three bladed inducers [1][2][3][6][7][8][9] and at some four bladed inducers. 10,11) CS has been studied by several researchers.…”

Section: Introductionmentioning

confidence: 86%

Experimental Study on Cavitation Instabilities of Small Turbopump for Rocket Engine

Hong

Choi

2017

Trans. Japan Soc. Aero. S Sci.

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A cavitation test was carried out for a fuel pump designated for a liquid rocket engine. The fuel enters the pump perpendicular to the direction of the shaft. Cavitation instabilities were investigated using an accelerometer installed on the pump casing and pressure transducers placed at the inlet and the outlet of the pump. Rotating cavitation appeared at a frequency faster than the pump rotational frequency, and cavitation surge appeared at a slower frequency. Cavitation surge appeared within the range of cavitation coefficients where rotating cavitation occurred. The frequencies of the rotating cavitation and the cavitation surge decreased as the cavitation coefficient and flow rate decreased, and were proportional to the rotational speed.

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“…The experiments were performed at a test facility at the Korea Aerospace Research Institute, specially developed for hydraulic and suction performance tests of inducers [9]. An outline of the closedloop test facility is shown in Fig.…”

Section: Inducer Design and Experimental Setupmentioning

confidence: 99%

Effects of a Bearing Strut on the Performance of a Turbopump Inducer

Choi

Noh

Kim

et al. 2006

Journal of Propulsion and Power

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Experimental and computational studies on an inducer with and without a bearing strut were performed to evaluate the effects of a strut on the performance of an inducer. Global performance data, such as head rise and efficiency, and detailed flow characteristics, such as surface static pressures, were measured and compared with computational results. Generally, a good agreement is observed between experimental and computational results, but some discrepancies are observed due to complex flow features such as backflows at the inlet and strut/inducer interactions. For the flow rates where the backflow region is large, installing a strut enhanced the hydraulic performance of the inducer by diminishing the size of the backflows. The results also show that the strut has negligible effect on the suction performance of the inducer. Nomenclature= inducer axial length at hub Q = volume flow rate r = dimensionless radius, r r h =r s r h U = speed of the blade z = axial coordinate = blade or relative flow angle = efficiency = cavitation number, 2p 1t p v =U 2 1t = flow coefficient,= tip or total z = axial direction 1 = inducer inlet 2 = inducer outlet

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Effect of Tip Clearance on the Cavitation Performance of a Turbopump Inducer

Cited by 29 publications

References 5 publications

Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Experimental Study on Cavitation Instabilities of Small Turbopump for Rocket Engine

Effects of a Bearing Strut on the Performance of a Turbopump Inducer

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