Design and test of an oxygen turbopump for a dual expander cycle rocket engine
A liquid oxygen (LOX) turbopump with an 860 degree R gaseous oxygen (GOX) turbine drive was designed for a 3750-lb thrust dual expander cycle rocket engine. This turbopump, which requires no interpropellant seals or system purges, features 156-hp, single-stage, full admission, impulse turbine; an ax...
Gespeichert in:
| Veröffentlicht in: | Journal of propulsion and power 1992-01, Vol.8 (1), p.80-86 |
|---|---|
| Hauptverfasser: | , , , |
| Format: | Artikel |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | 86 |
|---|---|
| container_issue | 1 |
| container_start_page | 80 |
| container_title | Journal of propulsion and power |
| container_volume | 8 |
| creator | Buckmann, P. S Shrimp, N. R Viteri, F Proctor, M |
| description | A liquid oxygen (LOX) turbopump with an 860 degree R gaseous oxygen (GOX) turbine drive was designed for a 3750-lb thrust dual expander cycle rocket engine. This turbopump, which requires no interpropellant seals or system purges, features 156-hp, single-stage, full admission, impulse turbine; an axial flow inducer; a two-stage centrifugal pump with unshrouded impellers; long-life, LOX-lubricated, self-aligning, hydrostatic bearings; and a subcritical rotor design. It is constructed of Monel, a nickel-copper alloy, which has low ignition potential in oxygen. |
| doi_str_mv | 10.2514/3.23445 |
| format | Article |
| fullrecord | <record><control><sourceid>proquest_aiaa_</sourceid><recordid>TN_cdi_proquest_journals_2312972486</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>25608494</sourcerecordid><originalsourceid>FETCH-LOGICAL-a429t-3b1e034a8bbf7b2276eb346153ca1d91cb02a62de730a0eff096f8181033be273</originalsourceid><addsrcrecordid>eNqN0U1rGzEQBmBRGqjrhv6BHgQpCTmsq6-VtMeQ5gtCcmnOQrs7Muuspa20C_a_r1IbDKaUnCSYR5p3GIS-UrJgJRU_-IJxIcoPaEZLzguulfyIZkQJXQhZ6k_oc0orQqjUUs3Q009I3dJj61s8QhpxcPmOw2a7BI_HKdZhmNYDdiFii9vJ9hg2Q9YQcbNtesAxNK8wYvDLzsMXdOJsn-B0f87Ry-3Nr-v74vH57uH66rGwglVjwWsKhAur69qpmjEloeZC5sCNpW1Fm5owK1kLihNLwDlSSaeppoTzGpjic3Sx-3eI4feUc5t1lxroe-shTMkoURLJaMmyPP-vZKUklS7Vu6AWlcjw7AiuwhR9HtcwTlmlmNDykLCJIaUIzgyxW9u4NZSYt0UZbv4uKstvO-ltssaPMRlaVYwQrgXXuXy5K9vO2kOr_WsztM64qe9H2IzZfv-XPe74B5nPpQU</addsrcrecordid><sourcetype>Aggregation Database</sourcetype><iscdi>true</iscdi><recordtype>article</recordtype><pqid>2312972486</pqid></control><display><type>article</type><title>Design and test of an oxygen turbopump for a dual expander cycle rocket engine</title><source>NASA Technical Reports Server</source><source>Alma/SFX Local Collection</source><creator>Buckmann, P. S ; Shrimp, N. R ; Viteri, F ; Proctor, M</creator><creatorcontrib>Buckmann, P. S ; Shrimp, N. R ; Viteri, F ; Proctor, M</creatorcontrib><description>A liquid oxygen (LOX) turbopump with an 860 degree R gaseous oxygen (GOX) turbine drive was designed for a 3750-lb thrust dual expander cycle rocket engine. This turbopump, which requires no interpropellant seals or system purges, features 156-hp, single-stage, full admission, impulse turbine; an axial flow inducer; a two-stage centrifugal pump with unshrouded impellers; long-life, LOX-lubricated, self-aligning, hydrostatic bearings; and a subcritical rotor design. It is constructed of Monel, a nickel-copper alloy, which has low ignition potential in oxygen.</description><identifier>ISSN: 0748-4658</identifier><identifier>EISSN: 1533-3876</identifier><identifier>DOI: 10.2514/3.23445</identifier><language>eng</language><publisher>Legacy CDMS: American Institute of Aeronautics and Astronautics</publisher><subject>design ; nickel alloys ; Rocket engines ; Spacecraft Propulsion And Power ; Turbine pumps ; turbopumps</subject><ispartof>Journal of propulsion and power, 1992-01, Vol.8 (1), p.80-86</ispartof><rights>Copyright American Institute of Aeronautics and Astronautics Jan/Feb 1992</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a429t-3b1e034a8bbf7b2276eb346153ca1d91cb02a62de730a0eff096f8181033be273</citedby><cites>FETCH-LOGICAL-a429t-3b1e034a8bbf7b2276eb346153ca1d91cb02a62de730a0eff096f8181033be273</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27901,27902</link.rule.ids></links><search><creatorcontrib>Buckmann, P. S</creatorcontrib><creatorcontrib>Shrimp, N. R</creatorcontrib><creatorcontrib>Viteri, F</creatorcontrib><creatorcontrib>Proctor, M</creatorcontrib><title>Design and test of an oxygen turbopump for a dual expander cycle rocket engine</title><title>Journal of propulsion and power</title><description>A liquid oxygen (LOX) turbopump with an 860 degree R gaseous oxygen (GOX) turbine drive was designed for a 3750-lb thrust dual expander cycle rocket engine. This turbopump, which requires no interpropellant seals or system purges, features 156-hp, single-stage, full admission, impulse turbine; an axial flow inducer; a two-stage centrifugal pump with unshrouded impellers; long-life, LOX-lubricated, self-aligning, hydrostatic bearings; and a subcritical rotor design. It is constructed of Monel, a nickel-copper alloy, which has low ignition potential in oxygen.</description><subject>design</subject><subject>nickel alloys</subject><subject>Rocket engines</subject><subject>Spacecraft Propulsion And Power</subject><subject>Turbine pumps</subject><subject>turbopumps</subject><issn>0748-4658</issn><issn>1533-3876</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>1992</creationdate><recordtype>article</recordtype><sourceid>CYI</sourceid><recordid>eNqN0U1rGzEQBmBRGqjrhv6BHgQpCTmsq6-VtMeQ5gtCcmnOQrs7Muuspa20C_a_r1IbDKaUnCSYR5p3GIS-UrJgJRU_-IJxIcoPaEZLzguulfyIZkQJXQhZ6k_oc0orQqjUUs3Q009I3dJj61s8QhpxcPmOw2a7BI_HKdZhmNYDdiFii9vJ9hg2Q9YQcbNtesAxNK8wYvDLzsMXdOJsn-B0f87Ry-3Nr-v74vH57uH66rGwglVjwWsKhAur69qpmjEloeZC5sCNpW1Fm5owK1kLihNLwDlSSaeppoTzGpjic3Sx-3eI4feUc5t1lxroe-shTMkoURLJaMmyPP-vZKUklS7Vu6AWlcjw7AiuwhR9HtcwTlmlmNDykLCJIaUIzgyxW9u4NZSYt0UZbv4uKstvO-ltssaPMRlaVYwQrgXXuXy5K9vO2kOr_WsztM64qe9H2IzZfv-XPe74B5nPpQU</recordid><startdate>19920101</startdate><enddate>19920101</enddate><creator>Buckmann, P. S</creator><creator>Shrimp, N. R</creator><creator>Viteri, F</creator><creator>Proctor, M</creator><general>American Institute of Aeronautics and Astronautics</general><scope>CYE</scope><scope>CYI</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope><scope>7TC</scope></search><sort><creationdate>19920101</creationdate><title>Design and test of an oxygen turbopump for a dual expander cycle rocket engine</title><author>Buckmann, P. S ; Shrimp, N. R ; Viteri, F ; Proctor, M</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a429t-3b1e034a8bbf7b2276eb346153ca1d91cb02a62de730a0eff096f8181033be273</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>1992</creationdate><topic>design</topic><topic>nickel alloys</topic><topic>Rocket engines</topic><topic>Spacecraft Propulsion And Power</topic><topic>Turbine pumps</topic><topic>turbopumps</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Buckmann, P. S</creatorcontrib><creatorcontrib>Shrimp, N. R</creatorcontrib><creatorcontrib>Viteri, F</creatorcontrib><creatorcontrib>Proctor, M</creatorcontrib><collection>NASA Scientific and Technical Information</collection><collection>NASA Technical Reports Server</collection><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Mechanical Engineering Abstracts</collection><jtitle>Journal of propulsion and power</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Buckmann, P. S</au><au>Shrimp, N. R</au><au>Viteri, F</au><au>Proctor, M</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Design and test of an oxygen turbopump for a dual expander cycle rocket engine</atitle><jtitle>Journal of propulsion and power</jtitle><date>1992-01-01</date><risdate>1992</risdate><volume>8</volume><issue>1</issue><spage>80</spage><epage>86</epage><pages>80-86</pages><issn>0748-4658</issn><eissn>1533-3876</eissn><abstract>A liquid oxygen (LOX) turbopump with an 860 degree R gaseous oxygen (GOX) turbine drive was designed for a 3750-lb thrust dual expander cycle rocket engine. This turbopump, which requires no interpropellant seals or system purges, features 156-hp, single-stage, full admission, impulse turbine; an axial flow inducer; a two-stage centrifugal pump with unshrouded impellers; long-life, LOX-lubricated, self-aligning, hydrostatic bearings; and a subcritical rotor design. It is constructed of Monel, a nickel-copper alloy, which has low ignition potential in oxygen.</abstract><cop>Legacy CDMS</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/3.23445</doi><tpages>7</tpages></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 0748-4658 |
| ispartof | Journal of propulsion and power, 1992-01, Vol.8 (1), p.80-86 |
| issn | 0748-4658 1533-3876 |
| language | eng |
| recordid | cdi_proquest_journals_2312972486 |
| source | NASA Technical Reports Server; Alma/SFX Local Collection |
| subjects | design nickel alloys Rocket engines Spacecraft Propulsion And Power Turbine pumps turbopumps |
| title | Design and test of an oxygen turbopump for a dual expander cycle rocket engine |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-05T17%3A11%3A12IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-proquest_aiaa_&rft_val_fmt=info:ofi/fmt:kev:mtx:journal&rft.genre=article&rft.atitle=Design%20and%20test%20of%20an%20oxygen%20turbopump%20for%20a%20dual%20expander%20cycle%20rocket%20engine&rft.jtitle=Journal%20of%20propulsion%20and%20power&rft.au=Buckmann,%20P.%20S&rft.date=1992-01-01&rft.volume=8&rft.issue=1&rft.spage=80&rft.epage=86&rft.pages=80-86&rft.issn=0748-4658&rft.eissn=1533-3876&rft_id=info:doi/10.2514/3.23445&rft_dat=%3Cproquest_aiaa_%3E25608494%3C/proquest_aiaa_%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_pqid=2312972486&rft_id=info:pmid/&rfr_iscdi=true |