GAS TURBINE ENGINE
A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan b...
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| creator | Baralon, Stephane Phelps, Benedict |
| description | A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each of the tandem fan blades comprises a main fan blade and an auxiliary fan blade positioned at the rear of the main fan blade, such that, over substantially all of the auxiliary fan blade's radial span, the leading edge of the auxiliary fan blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem. The auxiliary fan blade is movable within a range of pitch angles relative to the main fan blade. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_EP3828384A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>EP3828384A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_EP3828384A13</originalsourceid><addsrcrecordid>eNrjZBBydwxWCAkNcvL0c1Vw9XMHUjwMrGmJOcWpvFCam0HBzTXE2UM3tSA_PrW4IDE5NS-1JN41wNjCyMLYwsTR0JgIJQD39x2T</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>GAS TURBINE ENGINE</title><source>esp@cenet</source><creator>Baralon, Stephane ; Phelps, Benedict</creator><creatorcontrib>Baralon, Stephane ; Phelps, Benedict</creatorcontrib><description>A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each of the tandem fan blades comprises a main fan blade and an auxiliary fan blade positioned at the rear of the main fan blade, such that, over substantially all of the auxiliary fan blade's radial span, the leading edge of the auxiliary fan blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem. The auxiliary fan blade is movable within a range of pitch angles relative to the main fan blade.</description><language>eng ; fre ; ger</language><subject>BLASTING ; COMBUSTION ENGINES ; ENGINE PLANTS IN GENERAL ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; NON-POSITIVE DISPLACEMENT PUMPS ; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS ; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS ; STEAM ENGINES ; WEAPONS</subject><creationdate>2021</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=20210602&DB=EPODOC&CC=EP&NR=3828384A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20210602&DB=EPODOC&CC=EP&NR=3828384A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Baralon, Stephane</creatorcontrib><creatorcontrib>Phelps, Benedict</creatorcontrib><title>GAS TURBINE ENGINE</title><description>A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each of the tandem fan blades comprises a main fan blade and an auxiliary fan blade positioned at the rear of the main fan blade, such that, over substantially all of the auxiliary fan blade's radial span, the leading edge of the auxiliary fan blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem. The auxiliary fan blade is movable within a range of pitch angles relative to the main fan blade.</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>NON-POSITIVE DISPLACEMENT PUMPS</subject><subject>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</subject><subject>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</subject><subject>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBBydwxWCAkNcvL0c1Vw9XMHUjwMrGmJOcWpvFCam0HBzTXE2UM3tSA_PrW4IDE5NS-1JN41wNjCyMLYwsTR0JgIJQD39x2T</recordid><startdate>20210602</startdate><enddate>20210602</enddate><creator>Baralon, Stephane</creator><creator>Phelps, Benedict</creator><scope>EVB</scope></search><sort><creationdate>20210602</creationdate><title>GAS TURBINE ENGINE</title><author>Baralon, Stephane ; Phelps, Benedict</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3828384A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2021</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>NON-POSITIVE DISPLACEMENT PUMPS</topic><topic>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</topic><topic>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</topic><topic>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Baralon, Stephane</creatorcontrib><creatorcontrib>Phelps, Benedict</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Baralon, Stephane</au><au>Phelps, Benedict</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE ENGINE</title><date>2021-06-02</date><risdate>2021</risdate><abstract>A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each of the tandem fan blades comprises a main fan blade and an auxiliary fan blade positioned at the rear of the main fan blade, such that, over substantially all of the auxiliary fan blade's radial span, the leading edge of the auxiliary fan blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem. The auxiliary fan blade is movable within a range of pitch angles relative to the main fan blade.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS |
| title | GAS TURBINE ENGINE |
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