Performance Evaluation of Small-scale Liquid Pump using a Radial Turbine with H2O2 Gas Generator

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dc.contributor.authorPark, Daejongko
dc.contributor.authorHeo, Seonukko
dc.contributor.authorCho, Hwangraeko
dc.contributor.authorKwon, Sejinko
dc.date.accessioned2016-05-16T02:37:01Z-
dc.date.available2016-05-16T02:37:01Z-
dc.date.created2015-09-21-
dc.date.created2015-09-21-
dc.date.created2015-09-21-
dc.date.issued2015-09-
dc.identifier.citationTRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, v.58, no.5, pp.253 - 260-
dc.identifier.issn0549-3811-
dc.identifier.urihttp://hdl.handle.net/10203/207309-
dc.description.abstractA gas-turbine-driven pump system was designed and tested. Pump systems are generally driven by an electric motor, but a gas turbine is occasionally used as the power source for high power and performance; for example, the turbopump of a liquid rocket propulsion system. For research on turbopumps, a gas generator, turbine, and pump are developed. After each component is developed, the performance should be confirmed with a link test. In the case of a turbopump, an axial turbine is applied to generate huge torque, but a radial inflow turbine was used in this research. A radial inflow turbine can be obtained easily and mass-produced. System analysis was conducted using a link test with all components at once. The turbine generated shaft power under steady operation of the gas generator, and the pump performance was measured using a stepped closing valve at the pump exit. Turbine heat loss was considered and a slip factor was applied to the impeller design to modify performance. This research shows the feasibility of developing a pump system operated by a radial inflow turbine and its application to a small turbopump for a hybrid rocket propulsion system and an air-independent system.-
dc.languageEnglish-
dc.publisherJAPAN SOC AERONAUT SPACE SCI-
dc.titlePerformance Evaluation of Small-scale Liquid Pump using a Radial Turbine with H2O2 Gas Generator-
dc.typeArticle-
dc.identifier.wosid000360446800001-
dc.identifier.scopusid2-s2.0-84940643917-
dc.type.rimsART-
dc.citation.volume58-
dc.citation.issue5-
dc.citation.beginningpage253-
dc.citation.endingpage260-
dc.citation.publicationnameTRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES-
dc.contributor.localauthorKwon, Sejin-
dc.contributor.nonIdAuthorCho, Hwangrae-
dc.description.isOpenAccessN-
dc.type.journalArticleArticle-
dc.subject.keywordAuthorRadial Inflow Gas Turbine-
dc.subject.keywordAuthorLiquid Pump-
dc.subject.keywordAuthorHydrogen Peroxide-
dc.subject.keywordAuthorGas Generator-
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AE-Journal Papers(저널논문)
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