VANE FOR AN AIRCRAFT TURBINE ENGINE
A rotor vane for an aircraft turbine engine includes a blade extending between an inner platform and an outer platform which carries at least one projecting lip. The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral...
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| creator | MALLAT-DESMORTIERS, Jean-Philippe GARREAU, Edouard Emmanuel TSASSIS, Thomas DESBOIS, Lucas Geoffrey JEANTY, Peter Shamma DELCOIGNE, Eric Jacques JUGE, Samuel Laurent Noël Mathieu |
| description | A rotor vane for an aircraft turbine engine includes a blade extending between an inner platform and an outer platform which carries at least one projecting lip. The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral edges configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes. Each of the lateral edges has an anti-wear coating, and one of the lateral edges forms a hollow tip (P) with a bowl configured to receive the coating and further including a first concave cylindrical surface portion, the geometric dimensions of which are optimized to limit the risk of cracks appearing when the coating is applied. |
| format | Patent |
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The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral edges configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes. Each of the lateral edges has an anti-wear coating, and one of the lateral edges forms a hollow tip (P) with a bowl configured to receive the coating and further including a first concave cylindrical surface portion, the geometric dimensions of which are optimized to limit the risk of cracks appearing when the coating is applied.</description><language>eng ; fre ; ger</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>2023</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=20231227&DB=EPODOC&CC=EP&NR=4100624B1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20231227&DB=EPODOC&CC=EP&NR=4100624B1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MALLAT-DESMORTIERS, Jean-Philippe</creatorcontrib><creatorcontrib>GARREAU, Edouard Emmanuel</creatorcontrib><creatorcontrib>TSASSIS, Thomas</creatorcontrib><creatorcontrib>DESBOIS, Lucas Geoffrey</creatorcontrib><creatorcontrib>JEANTY, Peter Shamma</creatorcontrib><creatorcontrib>DELCOIGNE, Eric Jacques</creatorcontrib><creatorcontrib>JUGE, Samuel Laurent Noël Mathieu</creatorcontrib><title>VANE FOR AN AIRCRAFT TURBINE ENGINE</title><description>A rotor vane for an aircraft turbine engine includes a blade extending between an inner platform and an outer platform which carries at least one projecting lip. The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral edges configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes. Each of the lateral edges has an anti-wear coating, and one of the lateral edges forms a hollow tip (P) with a bowl configured to receive the coating and further including a first concave cylindrical surface portion, the geometric dimensions of which are optimized to limit the risk of cracks appearing when the coating is applied.</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>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFAOc_RzVXDzD1Jw9FNw9AxyDnJ0C1EICQ1y8gSKu_q5AykeBta0xJziVF4ozc2g4OYa4uyhm1qQH59aXJCYnJqXWhLvGmBiaGBgZmTiZGhMhBIA9Eoh8Q</recordid><startdate>20231227</startdate><enddate>20231227</enddate><creator>MALLAT-DESMORTIERS, Jean-Philippe</creator><creator>GARREAU, Edouard Emmanuel</creator><creator>TSASSIS, Thomas</creator><creator>DESBOIS, Lucas Geoffrey</creator><creator>JEANTY, Peter Shamma</creator><creator>DELCOIGNE, Eric Jacques</creator><creator>JUGE, Samuel Laurent Noël Mathieu</creator><scope>EVB</scope></search><sort><creationdate>20231227</creationdate><title>VANE FOR AN AIRCRAFT TURBINE ENGINE</title><author>MALLAT-DESMORTIERS, Jean-Philippe ; GARREAU, Edouard Emmanuel ; TSASSIS, Thomas ; DESBOIS, Lucas Geoffrey ; JEANTY, Peter Shamma ; DELCOIGNE, Eric Jacques ; JUGE, Samuel Laurent Noël Mathieu</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP4100624B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2023</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>MALLAT-DESMORTIERS, Jean-Philippe</creatorcontrib><creatorcontrib>GARREAU, Edouard Emmanuel</creatorcontrib><creatorcontrib>TSASSIS, Thomas</creatorcontrib><creatorcontrib>DESBOIS, Lucas Geoffrey</creatorcontrib><creatorcontrib>JEANTY, Peter Shamma</creatorcontrib><creatorcontrib>DELCOIGNE, Eric Jacques</creatorcontrib><creatorcontrib>JUGE, Samuel Laurent Noël Mathieu</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MALLAT-DESMORTIERS, Jean-Philippe</au><au>GARREAU, Edouard Emmanuel</au><au>TSASSIS, Thomas</au><au>DESBOIS, Lucas Geoffrey</au><au>JEANTY, Peter Shamma</au><au>DELCOIGNE, Eric Jacques</au><au>JUGE, Samuel Laurent Noël Mathieu</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>VANE FOR AN AIRCRAFT TURBINE ENGINE</title><date>2023-12-27</date><risdate>2023</risdate><abstract>A rotor vane for an aircraft turbine engine includes a blade extending between an inner platform and an outer platform which carries at least one projecting lip. The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral edges configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes. Each of the lateral edges has an anti-wear coating, and one of the lateral edges forms a hollow tip (P) with a bowl configured to receive the coating and further including a first concave cylindrical surface portion, the geometric dimensions of which are optimized to limit the risk of cracks appearing when the coating is applied.</abstract><oa>free_for_read</oa></addata></record> |
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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 AN AIRCRAFT TURBINE ENGINE |
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