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ISSN Online: 2688-7231

ISBN Online: 978-1-56700-524-0

Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India
December, 17-20, 2021, IIT Madras, Chennai, India

Cavitation Performance of a Cryogenic Upper Stage Liquid Rocket Engine Pump Operating in Liquid Hydrogen

Get access (open in a dialog) DOI: 10.1615/IHMTC-2021.2170
pages 1437-1442

要約

The present paper gives the comparative cavitation performance of a cryogenic upper stage rocket engine liquid hydrogen pump when operated in liquid hydrogen at a fluid temperature of 21.3K against the cavitation performance obtained for the same pump operated in room temperature water. Cavitation tests for the pump with water and liquid hydrogen were carried out simulating the condition corresponding to the pump operating condition expected in flight. The value of NPSH required for the pump with liquid hydrogen is observed to be 32 m against the NPSH requirement of 63 m based on water test data. This indicates that there is an improvement of about 50% in the cavitation performance of the pump with liquid hydrogen compared to water. This improvement in liquid hydrogen condition is reported worldwide and is due to the exemplary 'thermodynamic suppression head' characteristics of the fluid. Thus, pump operation at much lower inlet pressure is possible with liquid hydrogen without an appreciable loss in the performance of the pump. This paper gives the details of the test article (a liquid hydrogen pump for rocket engine), cavitation test facility scheme, test procedure and tests carried out with liquid hydrogen and water. The test results obtained are also discussed and the remarkable improvement obtained with liquid hydrogen is highlighted.