GAS TURBINE ENGINE
A gas turbine engine (20;100;120;140;150;170) comprises a fan rotor (42;174) having fan blades (98;134) received within an outer nacelle (94;122;145;172), and the outer nacelle (94...172) having an inner surface (132;151). A distance (L) is defined between an axial outer end (B) of the nacelle (94.....
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| creator | MURPHY, Michael Joseph SCHWARZ, Frederick M |
| description | A gas turbine engine (20;100;120;140;150;170) comprises a fan rotor (42;174) having fan blades (98;134) received within an outer nacelle (94;122;145;172), and the outer nacelle (94...172) having an inner surface (132;151). A distance (L) is defined between an axial outer end (B) of the nacelle (94...172), and a leading edge (102) of the fan blades (98;134). An anti-icing treatment is provided to an inner periphery of the nacelle (94...172) over at least 75% of the distance (L) along the inner periphery of the nacelle (94...172). |
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A distance (L) is defined between an axial outer end (B) of the nacelle (94...172), and a leading edge (102) of the fan blades (98;134). An anti-icing treatment is provided to an inner periphery of the nacelle (94...172) over at least 75% of the distance (L) along the inner periphery of the nacelle (94...172).</description><language>eng ; fre ; ger</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2022</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220420&DB=EPODOC&CC=EP&NR=3181865B1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220420&DB=EPODOC&CC=EP&NR=3181865B1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MURPHY, Michael Joseph</creatorcontrib><creatorcontrib>SCHWARZ, Frederick M</creatorcontrib><title>GAS TURBINE ENGINE</title><description>A gas turbine engine (20;100;120;140;150;170) comprises a fan rotor (42;174) having fan blades (98;134) received within an outer nacelle (94;122;145;172), and the outer nacelle (94...172) having an inner surface (132;151). A distance (L) is defined between an axial outer end (B) of the nacelle (94...172), and a leading edge (102) of the fan blades (98;134). An anti-icing treatment is provided to an inner periphery of the nacelle (94...172) over at least 75% of the distance (L) along the inner periphery of the nacelle (94...172).</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBBydwxWCAkNcvL0c1Vw9XMHUjwMrGmJOcWpvFCam0HBzTXE2UM3tSA_PrW4IDE5NS-1JN41wNjQwtDCzNTJ0JgIJQD3RB2N</recordid><startdate>20220420</startdate><enddate>20220420</enddate><creator>MURPHY, Michael Joseph</creator><creator>SCHWARZ, Frederick M</creator><scope>EVB</scope></search><sort><creationdate>20220420</creationdate><title>GAS TURBINE ENGINE</title><author>MURPHY, Michael Joseph ; SCHWARZ, Frederick M</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3181865B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2022</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>MURPHY, Michael Joseph</creatorcontrib><creatorcontrib>SCHWARZ, Frederick M</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MURPHY, Michael Joseph</au><au>SCHWARZ, Frederick M</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE ENGINE</title><date>2022-04-20</date><risdate>2022</risdate><abstract>A gas turbine engine (20;100;120;140;150;170) comprises a fan rotor (42;174) having fan blades (98;134) received within an outer nacelle (94;122;145;172), and the outer nacelle (94...172) having an inner surface (132;151). A distance (L) is defined between an axial outer end (B) of the nacelle (94...172), and a leading edge (102) of the fan blades (98;134). An anti-icing treatment is provided to an inner periphery of the nacelle (94...172) over at least 75% of the distance (L) along the inner periphery of the nacelle (94...172).</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| source | esp@cenet |
| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | GAS TURBINE ENGINE |
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