Testing of fuel/oxidizer-rich, high-pressure preburners
Results of an evaluation of high pressure combustion of fuel rich and oxidizer rich LOX/RP-1 propellants using 4.0 inch diameter prototype preburner injectors and chambers are presented. Testing covered a pressure range from 8.9 to 17.5 MN/square meters (1292 to 2540 psia). Fuel rich mixture ratios...
Gespeichert in:
| 1. Verfasser: | |
|---|---|
| Format: | Report |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | Lawver, B. R. |
| description | Results of an evaluation of high pressure combustion of fuel rich and oxidizer rich LOX/RP-1 propellants using 4.0 inch diameter prototype preburner injectors and chambers are presented. Testing covered a pressure range from 8.9 to 17.5 MN/square meters (1292 to 2540 psia). Fuel rich mixture ratios ranged from 0.238 to 0.367; oxidizer rich mixture ratios ranged from 27.2 to 47.5. Performance, gas temperature uniformity, and stability data for two fuel rich and two ozidizer rich preburner injectors are presented for a conventional like-on-like (LOL) design and a platelet design injector. Kinetically limited combustion is shown by the excellent agreement of measured fuel rich gas composition and C performance data with kinetic model predictions. The oxidizer rich test results support previous equilibrium combustion predictions. |
| format | Report |
| fullrecord | <record><control><sourceid>nasa_CYI</sourceid><recordid>TN_cdi_nasa_ntrs_19820016477</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>19820016477</sourcerecordid><originalsourceid>FETCH-nasa_ntrs_198200164773</originalsourceid><addsrcrecordid>eNrjZDAPSS0uycxLV8hPU0grTc3Rz6_ITMmsSi3SLcpMztBRyMhMz9AtKEotLi4tSlUAMpJKi_JSi4p5GFjTEnOKU3mhNDeDjJtriLOHbl5icWJ8XklRcbyhpYWRgYGhmYm5uTEBaQD_Yyov</addsrcrecordid><sourcetype>Publisher</sourcetype><iscdi>true</iscdi><recordtype>report</recordtype></control><display><type>report</type><title>Testing of fuel/oxidizer-rich, high-pressure preburners</title><source>NASA Technical Reports Server</source><creator>Lawver, B. R.</creator><creatorcontrib>Lawver, B. R.</creatorcontrib><description>Results of an evaluation of high pressure combustion of fuel rich and oxidizer rich LOX/RP-1 propellants using 4.0 inch diameter prototype preburner injectors and chambers are presented. Testing covered a pressure range from 8.9 to 17.5 MN/square meters (1292 to 2540 psia). Fuel rich mixture ratios ranged from 0.238 to 0.367; oxidizer rich mixture ratios ranged from 27.2 to 47.5. Performance, gas temperature uniformity, and stability data for two fuel rich and two ozidizer rich preburner injectors are presented for a conventional like-on-like (LOL) design and a platelet design injector. Kinetically limited combustion is shown by the excellent agreement of measured fuel rich gas composition and C performance data with kinetic model predictions. The oxidizer rich test results support previous equilibrium combustion predictions.</description><language>eng</language><publisher>Legacy CDMS</publisher><subject>Propellants And Fuels</subject><creationdate>1982</creationdate><rights>Copyright Determination: GOV_PUBLIC_USE_PERMITTED</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>776,796,4476</link.rule.ids><linktorsrc>$$Uhttps://ntrs.nasa.gov/citations/19820016477$$EView_record_in_NASA$$FView_record_in_$$GNASA$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Lawver, B. R.</creatorcontrib><title>Testing of fuel/oxidizer-rich, high-pressure preburners</title><description>Results of an evaluation of high pressure combustion of fuel rich and oxidizer rich LOX/RP-1 propellants using 4.0 inch diameter prototype preburner injectors and chambers are presented. Testing covered a pressure range from 8.9 to 17.5 MN/square meters (1292 to 2540 psia). Fuel rich mixture ratios ranged from 0.238 to 0.367; oxidizer rich mixture ratios ranged from 27.2 to 47.5. Performance, gas temperature uniformity, and stability data for two fuel rich and two ozidizer rich preburner injectors are presented for a conventional like-on-like (LOL) design and a platelet design injector. Kinetically limited combustion is shown by the excellent agreement of measured fuel rich gas composition and C performance data with kinetic model predictions. The oxidizer rich test results support previous equilibrium combustion predictions.</description><subject>Propellants And Fuels</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1982</creationdate><recordtype>report</recordtype><sourceid>CYI</sourceid><recordid>eNrjZDAPSS0uycxLV8hPU0grTc3Rz6_ITMmsSi3SLcpMztBRyMhMz9AtKEotLi4tSlUAMpJKi_JSi4p5GFjTEnOKU3mhNDeDjJtriLOHbl5icWJ8XklRcbyhpYWRgYGhmYm5uTEBaQD_Yyov</recordid><startdate>19820501</startdate><enddate>19820501</enddate><creator>Lawver, B. R.</creator><scope>CYE</scope><scope>CYI</scope></search><sort><creationdate>19820501</creationdate><title>Testing of fuel/oxidizer-rich, high-pressure preburners</title><author>Lawver, B. R.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-nasa_ntrs_198200164773</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1982</creationdate><topic>Propellants And Fuels</topic><toplevel>online_resources</toplevel><creatorcontrib>Lawver, B. R.</creatorcontrib><collection>NASA Scientific and Technical Information</collection><collection>NASA Technical Reports Server</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Lawver, B. R.</au><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Testing of fuel/oxidizer-rich, high-pressure preburners</btitle><date>1982-05-01</date><risdate>1982</risdate><abstract>Results of an evaluation of high pressure combustion of fuel rich and oxidizer rich LOX/RP-1 propellants using 4.0 inch diameter prototype preburner injectors and chambers are presented. Testing covered a pressure range from 8.9 to 17.5 MN/square meters (1292 to 2540 psia). Fuel rich mixture ratios ranged from 0.238 to 0.367; oxidizer rich mixture ratios ranged from 27.2 to 47.5. Performance, gas temperature uniformity, and stability data for two fuel rich and two ozidizer rich preburner injectors are presented for a conventional like-on-like (LOL) design and a platelet design injector. Kinetically limited combustion is shown by the excellent agreement of measured fuel rich gas composition and C performance data with kinetic model predictions. The oxidizer rich test results support previous equilibrium combustion predictions.</abstract><cop>Legacy CDMS</cop><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_nasa_ntrs_19820016477 |
| source | NASA Technical Reports Server |
| subjects | Propellants And Fuels |
| title | Testing of fuel/oxidizer-rich, high-pressure preburners |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-08T11%3A12%3A54IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-nasa_CYI&rft_val_fmt=info:ofi/fmt:kev:mtx:book&rft.genre=unknown&rft.btitle=Testing%20of%20fuel/oxidizer-rich,%20high-pressure%20preburners&rft.au=Lawver,%20B.%20R.&rft.date=1982-05-01&rft_id=info:doi/&rft_dat=%3Cnasa_CYI%3E19820016477%3C/nasa_CYI%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |