VANE FOR A TURBINE ENGINE WITH OPTIMISED ROOT AND METHOD FOR OPTIMISING A VANE PROFILE
The invention relates to a vane for a turbine engine of an aircraft comprising a blade having a lower surface and an upper surface that are connected upstream, in a direction of circulation of a gas in the turbine engine, by a leading edge and downstream by a trailing edge, the blade having a root a...
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| creator | MAXIME ELSA GIVERT MAXIME DAMOUR CHRISTOPHE GIMEL ALEXANDRE TRAHOT DENIS |
| description | The invention relates to a vane for a turbine engine of an aircraft comprising a blade having a lower surface and an upper surface that are connected upstream, in a direction of circulation of a gas in the turbine engine, by a leading edge and downstream by a trailing edge, the blade having a root at a radially external end and comprising a transverse head section (ST) in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first centre of gravity (G1). According to the invention, the root has a second centre of gravity (G2), which is defined in a plane parallel to the transverse head section and which is at least transversely offset from the first centre of gravity, the second centre of gravity (G2) being defined in a predetermined zone (ZG) at least partly demarcated by a first straight line (L1) and a second straight line (L2) substantially forming a V that is open towards the lower surface (10) and that comprises a peak, the orthogonal projection of which on |
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According to the invention, the root has a second centre of gravity (G2), which is defined in a plane parallel to the transverse head section and which is at least transversely offset from the first centre of gravity, the second centre of gravity (G2) being defined in a predetermined zone (ZG) at least partly demarcated by a first straight line (L1) and a second straight line (L2) substantially forming a V that is open towards the lower surface (10) and that comprises a peak, the orthogonal projection of which on</description><language>chi ; eng</language><subject>BLASTING ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; 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=20220222&DB=EPODOC&CC=CN&NR=114080489A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220222&DB=EPODOC&CC=CN&NR=114080489A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MAXIME ELSA</creatorcontrib><creatorcontrib>GIVERT MAXIME</creatorcontrib><creatorcontrib>DAMOUR CHRISTOPHE</creatorcontrib><creatorcontrib>GIMEL ALEXANDRE</creatorcontrib><creatorcontrib>TRAHOT DENIS</creatorcontrib><title>VANE FOR A TURBINE ENGINE WITH OPTIMISED ROOT AND METHOD FOR OPTIMISING A VANE PROFILE</title><description>The invention relates to a vane for a turbine engine of an aircraft comprising a blade having a lower surface and an upper surface that are connected upstream, in a direction of circulation of a gas in the turbine engine, by a leading edge and downstream by a trailing edge, the blade having a root at a radially external end and comprising a transverse head section (ST) in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first centre of gravity (G1). According to the invention, the root has a second centre of gravity (G2), which is defined in a plane parallel to the transverse head section and which is at least transversely offset from the first centre of gravity, the second centre of gravity (G2) being defined in a predetermined zone (ZG) at least partly demarcated by a first straight line (L1) and a second straight line (L2) substantially forming a V that is open towards the lower surface (10) and that comprises a peak, the orthogonal projection of which on</description><subject>BLASTING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</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>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZAgLc_RzVXDzD1JwVAgJDXLyBPJc_dxBVLhniIeCf0CIp69nsKuLQpC_f4iCo5-Lgq9riIe_C1gPVNbTzx2oHWxSQJC_m6ePKw8Da1piTnEqL5TmZlB0cw1x9tBNLciPTy0uSExOzUstiXf2MzQ0MbAwMLGwdDQmRg0AVwEwTA</recordid><startdate>20220222</startdate><enddate>20220222</enddate><creator>MAXIME ELSA</creator><creator>GIVERT MAXIME</creator><creator>DAMOUR CHRISTOPHE</creator><creator>GIMEL ALEXANDRE</creator><creator>TRAHOT DENIS</creator><scope>EVB</scope></search><sort><creationdate>20220222</creationdate><title>VANE FOR A TURBINE ENGINE WITH OPTIMISED ROOT AND METHOD FOR OPTIMISING A VANE PROFILE</title><author>MAXIME ELSA ; GIVERT MAXIME ; DAMOUR CHRISTOPHE ; GIMEL ALEXANDRE ; TRAHOT DENIS</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN114080489A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2022</creationdate><topic>BLASTING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</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>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>MAXIME ELSA</creatorcontrib><creatorcontrib>GIVERT MAXIME</creatorcontrib><creatorcontrib>DAMOUR CHRISTOPHE</creatorcontrib><creatorcontrib>GIMEL ALEXANDRE</creatorcontrib><creatorcontrib>TRAHOT DENIS</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MAXIME ELSA</au><au>GIVERT MAXIME</au><au>DAMOUR CHRISTOPHE</au><au>GIMEL ALEXANDRE</au><au>TRAHOT DENIS</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>VANE FOR A TURBINE ENGINE WITH OPTIMISED ROOT AND METHOD FOR OPTIMISING A VANE PROFILE</title><date>2022-02-22</date><risdate>2022</risdate><abstract>The invention relates to a vane for a turbine engine of an aircraft comprising a blade having a lower surface and an upper surface that are connected upstream, in a direction of circulation of a gas in the turbine engine, by a leading edge and downstream by a trailing edge, the blade having a root at a radially external end and comprising a transverse head section (ST) in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first centre of gravity (G1). According to the invention, the root has a second centre of gravity (G2), which is defined in a plane parallel to the transverse head section and which is at least transversely offset from the first centre of gravity, the second centre of gravity (G2) being defined in a predetermined zone (ZG) at least partly demarcated by a first straight line (L1) and a second straight line (L2) substantially forming a V that is open towards the lower surface (10) and that comprises a peak, the orthogonal projection of which on</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
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| subjects | BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | VANE FOR A TURBINE ENGINE WITH OPTIMISED ROOT AND METHOD FOR OPTIMISING A VANE PROFILE |
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