VARIABLE VANE OF AN AIRCRAFT TURBINE ENGINE STATOR, AND AIRCRAFT TURBINE ENGINE
The invention relates to a variable vane (9; 109) of a turbine engine stator, the vane comprising: a blade (11) for guiding an air stream; and one or two platforms (26) disposed at one end or at both ends of the blade, the platform or platforms comprising a surface (26.1) for guiding the air stream,...
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| creator | PRINCIVALLE, Rémy |
| description | The invention relates to a variable vane (9; 109) of a turbine engine stator, the vane comprising: a blade (11) for guiding an air stream; and one or two platforms (26) disposed at one end or at both ends of the blade, the platform or platforms comprising a surface (26.1) for guiding the air stream, the surface comprising a first disc portion (30.1) on the pressure side (11.3) and a second disc portion (30.2) on the suction side (11.4); characterised in that the first or second disc portion or at least one of the first or second disc portions comprises a boss (32).
L'invention propose une aube (9; 109) à calage variable de stator de turbomachine, l'aube comprenant : une pale (11) de guidage d'un flux d'air; et une ou deux plateforme(s) (26) disposée(s) à une extrémité ou aux deux extrémités de la pale, la ou les plateformes comprenant une surface de guidage (26.1) du flux d'air, la surface comprenant une première portion de disque (30.1) du côté de l'intrados (11.3) et une seconde portion de disque (30.2) du côté de l'extrados (11.4); remarquable en ce que la ou au moins une des premières ou secondes portions de disque comprend une bosse (32). |
| format | Patent |
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L'invention propose une aube (9; 109) à calage variable de stator de turbomachine, l'aube comprenant : une pale (11) de guidage d'un flux d'air; et une ou deux plateforme(s) (26) disposée(s) à une extrémité ou aux deux extrémités de la pale, la ou les plateformes comprenant une surface de guidage (26.1) du flux d'air, la surface comprenant une première portion de disque (30.1) du côté de l'intrados (11.3) et une seconde portion de disque (30.2) du côté de l'extrados (11.4); remarquable en ce que la ou au moins une des premières ou secondes portions de disque comprend une bosse (32).</description><language>eng ; fre</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>2024</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=20240215&DB=EPODOC&CC=WO&NR=2024033065A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240215&DB=EPODOC&CC=WO&NR=2024033065A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>PRINCIVALLE, Rémy</creatorcontrib><title>VARIABLE VANE OF AN AIRCRAFT TURBINE ENGINE STATOR, AND AIRCRAFT TURBINE ENGINE</title><description>The invention relates to a variable vane (9; 109) of a turbine engine stator, the vane comprising: a blade (11) for guiding an air stream; and one or two platforms (26) disposed at one end or at both ends of the blade, the platform or platforms comprising a surface (26.1) for guiding the air stream, the surface comprising a first disc portion (30.1) on the pressure side (11.3) and a second disc portion (30.2) on the suction side (11.4); characterised in that the first or second disc portion or at least one of the first or second disc portions comprises a boss (32).
L'invention propose une aube (9; 109) à calage variable de stator de turbomachine, l'aube comprenant : une pale (11) de guidage d'un flux d'air; et une ou deux plateforme(s) (26) disposée(s) à une extrémité ou aux deux extrémités de la pale, la ou les plateformes comprenant une surface de guidage (26.1) du flux d'air, la surface comprenant une première portion de disque (30.1) du côté de l'intrados (11.3) et une seconde portion de disque (30.2) du côté de l'extrados (11.4); remarquable en ce que la ou au moins une des premières ou secondes portions de disque comprend une bosse (32).</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>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPAPcwzydHTycVUIc_RzVfB3U3D0U3D0DHIOcnQLUQgJDXLyBAq7-rmDqOAQxxD_IB2gEhdcangYWNMSc4pTeaE0N4Oym2uIs4duakF-fGpxQWJyal5qSXy4v5GBkYmBsbGBmamjoTFxqgC02y8e</recordid><startdate>20240215</startdate><enddate>20240215</enddate><creator>PRINCIVALLE, Rémy</creator><scope>EVB</scope></search><sort><creationdate>20240215</creationdate><title>VARIABLE VANE OF AN AIRCRAFT TURBINE ENGINE STATOR, AND AIRCRAFT TURBINE ENGINE</title><author>PRINCIVALLE, Rémy</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_WO2024033065A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2024</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>PRINCIVALLE, Rémy</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>PRINCIVALLE, Rémy</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>VARIABLE VANE OF AN AIRCRAFT TURBINE ENGINE STATOR, AND AIRCRAFT TURBINE ENGINE</title><date>2024-02-15</date><risdate>2024</risdate><abstract>The invention relates to a variable vane (9; 109) of a turbine engine stator, the vane comprising: a blade (11) for guiding an air stream; and one or two platforms (26) disposed at one end or at both ends of the blade, the platform or platforms comprising a surface (26.1) for guiding the air stream, the surface comprising a first disc portion (30.1) on the pressure side (11.3) and a second disc portion (30.2) on the suction side (11.4); characterised in that the first or second disc portion or at least one of the first or second disc portions comprises a boss (32).
L'invention propose une aube (9; 109) à calage variable de stator de turbomachine, l'aube comprenant : une pale (11) de guidage d'un flux d'air; et une ou deux plateforme(s) (26) disposée(s) à une extrémité ou aux deux extrémités de la pale, la ou les plateformes comprenant une surface de guidage (26.1) du flux d'air, la surface comprenant une première portion de disque (30.1) du côté de l'intrados (11.3) et une seconde portion de disque (30.2) du côté de l'extrados (11.4); remarquable en ce que la ou au moins une des premières ou secondes portions de disque comprend une bosse (32).</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre |
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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 | VARIABLE VANE OF AN AIRCRAFT TURBINE ENGINE STATOR, AND AIRCRAFT TURBINE ENGINE |
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