DC Field | Value | Language |
---|---|---|
dc.contributor.author | Park, Daejong | ko |
dc.contributor.author | Heo, Seonuk | ko |
dc.contributor.author | Cho, Hwangrae | ko |
dc.contributor.author | Kwon, Sejin | ko |
dc.date.accessioned | 2016-05-16T02:37:01Z | - |
dc.date.available | 2016-05-16T02:37:01Z | - |
dc.date.created | 2015-09-21 | - |
dc.date.created | 2015-09-21 | - |
dc.date.created | 2015-09-21 | - |
dc.date.issued | 2015-09 | - |
dc.identifier.citation | TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, v.58, no.5, pp.253 - 260 | - |
dc.identifier.issn | 0549-3811 | - |
dc.identifier.uri | http://hdl.handle.net/10203/207309 | - |
dc.description.abstract | A 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.language | English | - |
dc.publisher | JAPAN SOC AERONAUT SPACE SCI | - |
dc.title | Performance Evaluation of Small-scale Liquid Pump using a Radial Turbine with H2O2 Gas Generator | - |
dc.type | Article | - |
dc.identifier.wosid | 000360446800001 | - |
dc.identifier.scopusid | 2-s2.0-84940643917 | - |
dc.type.rims | ART | - |
dc.citation.volume | 58 | - |
dc.citation.issue | 5 | - |
dc.citation.beginningpage | 253 | - |
dc.citation.endingpage | 260 | - |
dc.citation.publicationname | TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES | - |
dc.contributor.localauthor | Kwon, Sejin | - |
dc.contributor.nonIdAuthor | Cho, Hwangrae | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | Radial Inflow Gas Turbine | - |
dc.subject.keywordAuthor | Liquid Pump | - |
dc.subject.keywordAuthor | Hydrogen Peroxide | - |
dc.subject.keywordAuthor | Gas Generator | - |
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