METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT
The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surfaceextending between a leading edge and a trailing edge of the blade, the trailing edge having to have a...
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| creator | SABOUNDJI AMAR GIMEL ALEXANDRE SOISSON MARC LISOWSKI JANUSZ BOUKERMA SAID |
| description | The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surfaceextending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a).
本发明涉及一种用于生产用于飞行器涡轮机的金属叶片元件的方法，所述叶片元件包括至少一个叶片，该至少一个叶片具有在叶片的前缘和后缘之间延伸的上部表面和下部表面，后缘必须具有厚度X1，所述方法包括以下步骤：a)通过失蜡铸造生产叶片元件，以及b)对叶片元件进行精加工，其特征在于，步骤b)包括至少对叶片或每个叶片的后缘进行化学铣削，以便获得所述厚度X1，该厚度X1不能通过步骤a)直接获得。 |
| format | Patent |
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本发明涉及一种用于生产用于飞行器涡轮机的金属叶片元件的方法，所述叶片元件包括至少一个叶片，该至少一个叶片具有在叶片的前缘和后缘之间延伸的上部表面和下部表面，后缘必须具有厚度X1，所述方法包括以下步骤：a)通过失蜡铸造生产叶片元件，以及b)对叶片元件进行精加工，其特征在于，步骤b)包括至少对叶片或每个叶片的后缘进行化学铣削，以便获得所述厚度X1，该厚度X1不能通过步骤a)直接获得。</description><language>chi ; eng</language><subject>BLASTING ; CHEMICAL SURFACE TREATMENT ; CHEMISTRY ; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL ; COATING MATERIAL WITH METALLIC MATERIAL ; COATING METALLIC MATERIAL ; COMBINED OPERATIONS ; DIFFUSION TREATMENT OF METALLIC MATERIAL ; ENGINE PLANTS IN GENERAL ; HEATING ; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL ; LIGHTING ; MACHINE TOOLS ; MACHINES OR ENGINES IN GENERAL ; MEASURING ; MECHANICAL ENGINEERING ; METAL-WORKING NOT OTHERWISE PROVIDED FOR ; METALLURGY ; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLICMATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASSC23 AND AT LEAST ONEPROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25 ; NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; OTHER WORKING OF METAL ; PERFORMING OPERATIONS ; PHYSICS ; STEAM ENGINES ; TESTING ; TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES ; TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR ; TRANSPORTING ; UNIVERSAL MACHINE TOOLS ; WEAPONS</subject><creationdate>2020</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=20201215&DB=EPODOC&CC=CN&NR=112088228A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20201215&DB=EPODOC&CC=CN&NR=112088228A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>SABOUNDJI AMAR</creatorcontrib><creatorcontrib>GIMEL ALEXANDRE</creatorcontrib><creatorcontrib>SOISSON MARC</creatorcontrib><creatorcontrib>LISOWSKI JANUSZ</creatorcontrib><creatorcontrib>BOUKERMA SAID</creatorcontrib><title>METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT</title><description>The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surfaceextending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a).
本发明涉及一种用于生产用于飞行器涡轮机的金属叶片元件的方法，所述叶片元件包括至少一个叶片，该至少一个叶片具有在叶片的前缘和后缘之间延伸的上部表面和下部表面，后缘必须具有厚度X1，所述方法包括以下步骤：a)通过失蜡铸造生产叶片元件，以及b)对叶片元件进行精加工，其特征在于，步骤b)包括至少对叶片或每个叶片的后缘进行化学铣削，以便获得所述厚度X1，该厚度X1不能通过步骤a)直接获得。</description><subject>BLASTING</subject><subject>CHEMICAL SURFACE TREATMENT</subject><subject>CHEMISTRY</subject><subject>COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL</subject><subject>COATING MATERIAL WITH METALLIC MATERIAL</subject><subject>COATING METALLIC MATERIAL</subject><subject>COMBINED OPERATIONS</subject><subject>DIFFUSION TREATMENT OF METALLIC MATERIAL</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</subject><subject>INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL</subject><subject>LIGHTING</subject><subject>MACHINE TOOLS</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MEASURING</subject><subject>MECHANICAL ENGINEERING</subject><subject>METAL-WORKING NOT OTHERWISE PROVIDED FOR</subject><subject>METALLURGY</subject><subject>MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLICMATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASSC23 AND AT LEAST ONEPROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25</subject><subject>NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>OTHER WORKING OF METAL</subject><subject>PERFORMING OPERATIONS</subject><subject>PHYSICS</subject><subject>STEAM ENGINES</subject><subject>TESTING</subject><subject>TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES</subject><subject>TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR</subject><subject>TRANSPORTING</subject><subject>UNIVERSAL MACHINE TOOLS</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2020</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyjEKAjEQQNE0FqLeYTyA4MYm7exkYgLJREK2XhaJlejCen8U8QBWHz5vrVLi6rMFlwtcSrYDBTkDwmdjhD6iZQscObHUL0KoQ-lzQvJBGLIDFMBQqKCrW7W6Tfel7X7dqL3jSv7Q5ufYlnm6tkd7jSRdp4_GaG3w9I95A41mLXo</recordid><startdate>20201215</startdate><enddate>20201215</enddate><creator>SABOUNDJI AMAR</creator><creator>GIMEL ALEXANDRE</creator><creator>SOISSON MARC</creator><creator>LISOWSKI JANUSZ</creator><creator>BOUKERMA SAID</creator><scope>EVB</scope></search><sort><creationdate>20201215</creationdate><title>METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT</title><author>SABOUNDJI AMAR ; GIMEL ALEXANDRE ; SOISSON MARC ; LISOWSKI JANUSZ ; BOUKERMA SAID</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN112088228A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2020</creationdate><topic>BLASTING</topic><topic>CHEMICAL SURFACE TREATMENT</topic><topic>CHEMISTRY</topic><topic>COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL</topic><topic>COATING MATERIAL WITH METALLIC MATERIAL</topic><topic>COATING METALLIC MATERIAL</topic><topic>COMBINED OPERATIONS</topic><topic>DIFFUSION TREATMENT OF METALLIC MATERIAL</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</topic><topic>INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL</topic><topic>LIGHTING</topic><topic>MACHINE TOOLS</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MEASURING</topic><topic>MECHANICAL ENGINEERING</topic><topic>METAL-WORKING NOT OTHERWISE PROVIDED FOR</topic><topic>METALLURGY</topic><topic>MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLICMATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASSC23 AND AT LEAST ONEPROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25</topic><topic>NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>OTHER WORKING OF METAL</topic><topic>PERFORMING OPERATIONS</topic><topic>PHYSICS</topic><topic>STEAM ENGINES</topic><topic>TESTING</topic><topic>TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES</topic><topic>TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR</topic><topic>TRANSPORTING</topic><topic>UNIVERSAL MACHINE TOOLS</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>SABOUNDJI AMAR</creatorcontrib><creatorcontrib>GIMEL ALEXANDRE</creatorcontrib><creatorcontrib>SOISSON MARC</creatorcontrib><creatorcontrib>LISOWSKI JANUSZ</creatorcontrib><creatorcontrib>BOUKERMA SAID</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SABOUNDJI AMAR</au><au>GIMEL ALEXANDRE</au><au>SOISSON MARC</au><au>LISOWSKI JANUSZ</au><au>BOUKERMA SAID</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT</title><date>2020-12-15</date><risdate>2020</risdate><abstract>The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surfaceextending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a).
本发明涉及一种用于生产用于飞行器涡轮机的金属叶片元件的方法，所述叶片元件包括至少一个叶片，该至少一个叶片具有在叶片的前缘和后缘之间延伸的上部表面和下部表面，后缘必须具有厚度X1，所述方法包括以下步骤：a)通过失蜡铸造生产叶片元件，以及b)对叶片元件进行精加工，其特征在于，步骤b)包括至少对叶片或每个叶片的后缘进行化学铣削，以便获得所述厚度X1，该厚度X1不能通过步骤a)直接获得。</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING CHEMICAL SURFACE TREATMENT CHEMISTRY COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL COMBINED OPERATIONS DIFFUSION TREATMENT OF METALLIC MATERIAL ENGINE PLANTS IN GENERAL HEATING INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MEASURING MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR METALLURGY MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLICMATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASSC23 AND AT LEAST ONEPROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25 NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS PHYSICS STEAM ENGINES TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS |
| title | METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT |
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