Leading edge shield
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), which comprises a lower canopy fin (34) and an upper canopy fin (36), each extending in the height and length direction and connected together along their hei...
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| creator | RUF THIBAULT DIOGO GERALD ROMERO JEAN-LOUIS GUIVARC'H JEREMY BASSOT ALAIN JACQUES MICHEL |
| description | The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), which comprises a lower canopy fin (34) and an upper canopy fin (36), each extending in the height and length direction and connected together along their height, the lower canopy fin (34) having a greater length than the upper canopy fin (36) over a first segment (SI) of the leading edge shield (32), and a length equal to or lower than the upper canopy fin (36) over a second segment (S2) of the leading edge shield (32).
本发明涉及涡轮机叶片领域，更具体地涉及用于涡轮机叶片(16)的主边缘护罩(32)，该主边缘护罩(32)包括下盖翅片(34)和上盖翅片(36)，每个翅片均沿着高度和长度方向延伸，并沿着它们的高度连接在起，该下盖翅片(34)在主边缘护罩(32)的第部分(S1)上的长度大于上盖翅片(36)的长度，在主边缘护罩(32)的第二部分(S2)上的长度等于或小于上盖翅片(36)的长度。 |
| format | Patent |
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本发明涉及涡轮机叶片领域，更具体地涉及用于涡轮机叶片(16)的主边缘护罩(32)，该主边缘护罩(32)包括下盖翅片(34)和上盖翅片(36)，每个翅片均沿着高度和长度方向延伸，并沿着它们的高度连接在起，该下盖翅片(34)在主边缘护罩(32)的第部分(S1)上的长度大于上盖翅片(36)的长度，在主边缘护罩(32)的第二部分(S2)上的长度等于或小于上盖翅片(36)的长度。</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>2018</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=20180831&DB=EPODOC&CC=CN&NR=108474258A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180831&DB=EPODOC&CC=CN&NR=108474258A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>RUF THIBAULT</creatorcontrib><creatorcontrib>DIOGO GERALD</creatorcontrib><creatorcontrib>ROMERO JEAN-LOUIS</creatorcontrib><creatorcontrib>GUIVARC'H JEREMY</creatorcontrib><creatorcontrib>BASSOT ALAIN JACQUES MICHEL</creatorcontrib><title>Leading edge shield</title><description>The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), which comprises a lower canopy fin (34) and an upper canopy fin (36), each extending in the height and length direction and connected together along their height, the lower canopy fin (34) having a greater length than the upper canopy fin (36) over a first segment (SI) of the leading edge shield (32), and a length equal to or lower than the upper canopy fin (36) over a second segment (S2) of the leading edge shield (32).
本发明涉及涡轮机叶片领域，更具体地涉及用于涡轮机叶片(16)的主边缘护罩(32)，该主边缘护罩(32)包括下盖翅片(34)和上盖翅片(36)，每个翅片均沿着高度和长度方向延伸，并沿着它们的高度连接在起，该下盖翅片(34)在主边缘护罩(32)的第部分(S1)上的长度大于上盖翅片(36)的长度，在主边缘护罩(32)的第二部分(S2)上的长度等于或小于上盖翅片(36)的长度。</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>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBD2SU1MycxLV0hNSU9VKM7ITM1J4WFgTUvMKU7lhdLcDIpuriHOHrqpBfnxqcUFicmpeakl8c5-hgYWJuYmRqYWjsbEqAEA_nQgCg</recordid><startdate>20180831</startdate><enddate>20180831</enddate><creator>RUF THIBAULT</creator><creator>DIOGO GERALD</creator><creator>ROMERO JEAN-LOUIS</creator><creator>GUIVARC'H JEREMY</creator><creator>BASSOT ALAIN JACQUES MICHEL</creator><scope>EVB</scope></search><sort><creationdate>20180831</creationdate><title>Leading edge shield</title><author>RUF THIBAULT ; DIOGO GERALD ; ROMERO JEAN-LOUIS ; GUIVARC'H JEREMY ; BASSOT ALAIN JACQUES MICHEL</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN108474258A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2018</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>RUF THIBAULT</creatorcontrib><creatorcontrib>DIOGO GERALD</creatorcontrib><creatorcontrib>ROMERO JEAN-LOUIS</creatorcontrib><creatorcontrib>GUIVARC'H JEREMY</creatorcontrib><creatorcontrib>BASSOT ALAIN JACQUES MICHEL</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>RUF THIBAULT</au><au>DIOGO GERALD</au><au>ROMERO JEAN-LOUIS</au><au>GUIVARC'H JEREMY</au><au>BASSOT ALAIN JACQUES MICHEL</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Leading edge shield</title><date>2018-08-31</date><risdate>2018</risdate><abstract>The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), which comprises a lower canopy fin (34) and an upper canopy fin (36), each extending in the height and length direction and connected together along their height, the lower canopy fin (34) having a greater length than the upper canopy fin (36) over a first segment (SI) of the leading edge shield (32), and a length equal to or lower than the upper canopy fin (36) over a second segment (S2) of the leading edge shield (32).
本发明涉及涡轮机叶片领域，更具体地涉及用于涡轮机叶片(16)的主边缘护罩(32)，该主边缘护罩(32)包括下盖翅片(34)和上盖翅片(36)，每个翅片均沿着高度和长度方向延伸，并沿着它们的高度连接在起，该下盖翅片(34)在主边缘护罩(32)的第部分(S1)上的长度大于上盖翅片(36)的长度，在主边缘护罩(32)的第二部分(S2)上的长度等于或小于上盖翅片(36)的长度。</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
| recordid | cdi_epo_espacenet_CN108474258A |
| source | esp@cenet |
| 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 | Leading edge shield |
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