Gas turbine engine fan
1. Field of the Invention An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide...
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| creator | Giffin, III, Rollin George |
| description | 1. Field of the Invention
An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide vanes, a first stage of first fan rotor blades, a stage of first variable angle stator vanes, and a fan bleed. The inlet guide vanes are angled to block the linear line of sight of the rotating fan blades through the inlet and include a RAM treatment which preferably is a coating of a radar absorbing material on the surface of the inlet guide vanes. The exemplary embodiment has a multi-stage fan section with the mid-stage fan bleed disposed between the first and second stages of fan rotor blades. |
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An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide vanes, a first stage of first fan rotor blades, a stage of first variable angle stator vanes, and a fan bleed. The inlet guide vanes are angled to block the linear line of sight of the rotating fan blades through the inlet and include a RAM treatment which preferably is a coating of a radar absorbing material on the surface of the inlet guide vanes. The exemplary embodiment has a multi-stage fan section with the mid-stage fan bleed disposed between the first and second stages of fan rotor blades.</description><language>eng</language><creationdate>2003</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktopdf>$$Uhttps://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/6662546$$EPDF$$P50$$Guspatents$$Hfree_for_read</linktopdf><link.rule.ids>230,309,781,803,886,64044</link.rule.ids><linktorsrc>$$Uhttps://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/6662546$$EView_record_in_USPTO$$FView_record_in_$$GUSPTO$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Giffin, III, Rollin George</creatorcontrib><creatorcontrib>General Electric Company</creatorcontrib><title>Gas turbine engine fan</title><description>1. Field of the Invention
An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide vanes, a first stage of first fan rotor blades, a stage of first variable angle stator vanes, and a fan bleed. The inlet guide vanes are angled to block the linear line of sight of the rotating fan blades through the inlet and include a RAM treatment which preferably is a coating of a radar absorbing material on the surface of the inlet guide vanes. The exemplary embodiment has a multi-stage fan section with the mid-stage fan bleed disposed between the first and second stages of fan rotor blades.</description><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2003</creationdate><recordtype>patent</recordtype><sourceid>EFH</sourceid><recordid>eNrjZBBzTyxWKCktSsrMS1VIzUsHUWmJeTwMrGmJOcWpvFCam0HBzTXE2UO3tLggsSQ1r6Q4Pr0oEUQZmJmZGZmamBkToQQAZXMiEA</recordid><startdate>20031216</startdate><enddate>20031216</enddate><creator>Giffin, III, Rollin George</creator><scope>EFH</scope></search><sort><creationdate>20031216</creationdate><title>Gas turbine engine fan</title><author>Giffin, III, Rollin George</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-uspatents_grants_066625463</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2003</creationdate><toplevel>online_resources</toplevel><creatorcontrib>Giffin, III, Rollin George</creatorcontrib><creatorcontrib>General Electric Company</creatorcontrib><collection>USPTO Issued Patents</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Giffin, III, Rollin George</au><aucorp>General Electric Company</aucorp><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Gas turbine engine fan</title><date>2003-12-16</date><risdate>2003</risdate><abstract>1. Field of the Invention
An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide vanes, a first stage of first fan rotor blades, a stage of first variable angle stator vanes, and a fan bleed. The inlet guide vanes are angled to block the linear line of sight of the rotating fan blades through the inlet and include a RAM treatment which preferably is a coating of a radar absorbing material on the surface of the inlet guide vanes. The exemplary embodiment has a multi-stage fan section with the mid-stage fan bleed disposed between the first and second stages of fan rotor blades.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| source | USPTO Issued Patents |
| title | Gas turbine engine fan |
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