Machining method for cooling hole of turbine blade of heavy duty gas turbine with thermal barrier coating of double-ceramic-layer structure
The invention provides a method for processing a cooling hole of a turbine blade of a heavy duty gas turbine with a thermal barrier coating with a double-ceramic-layer structure, which comprises the following steps of: firstly, spraying the thermal barrier coating on the turbine blade by adopting a...
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| creator | LIU WEI SHU GUOGANG YU ZHIYONG GUO YUWEI SUN JIAN LI ZHENRUI MENG QINGYAN LEI YUEHUA YU HAIYUAN |
| description | The invention provides a method for processing a cooling hole of a turbine blade of a heavy duty gas turbine with a thermal barrier coating with a double-ceramic-layer structure, which comprises the following steps of: firstly, spraying the thermal barrier coating on the turbine blade by adopting a high velocity oxy-fuel spraying and atmosphere plasma spraying process by adopting a processing method of firstly coating and then punching; the thermal barrier coating structure of the second ceramic layer/the first ceramic layer/the bonding layer/the turbine blade base body is prepared; and then high-efficiency, high-quality and high-precision machining of the turbine blade air film cooling holes is achieved through the combined machining mode of long-pulse laser machining of round holes and ultrafast laser machining of forming holes, the machined cooling holes are uniform in hole diameter and good in consistency, and good industrial application prospects are achieved.
本发明提出一种带有双陶瓷层结构热障涂层的重型燃气轮机透平叶片冷却孔加工方法，通过采用"先 |
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本发明提出一种带有双陶瓷层结构热障涂层的重型燃气轮机透平叶片冷却孔加工方法，通过采用"先</description><language>chi ; eng</language><subject>APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TO SURFACES, IN GENERAL ; CLADDING OR PLATING BY SOLDERING OR WELDING ; COMBINED OPERATIONS ; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ; MACHINE TOOLS ; METAL-WORKING NOT OTHERWISE PROVIDED FOR ; OTHER WORKING OF METAL ; PERFORMING OPERATIONS ; PROCESSES FOR APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TOSURFACES, IN GENERAL ; SOLDERING OR UNSOLDERING ; SPRAYING OR ATOMISING IN GENERAL ; TRANSPORTING ; UNIVERSAL MACHINE TOOLS ; WELDING ; WORKING BY LASER BEAM</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=20240726&DB=EPODOC&CC=CN&NR=118385894A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240726&DB=EPODOC&CC=CN&NR=118385894A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>LIU WEI</creatorcontrib><creatorcontrib>SHU GUOGANG</creatorcontrib><creatorcontrib>YU ZHIYONG</creatorcontrib><creatorcontrib>GUO YUWEI</creatorcontrib><creatorcontrib>SUN JIAN</creatorcontrib><creatorcontrib>LI ZHENRUI</creatorcontrib><creatorcontrib>MENG QINGYAN</creatorcontrib><creatorcontrib>LEI YUEHUA</creatorcontrib><creatorcontrib>YU HAIYUAN</creatorcontrib><title>Machining method for cooling hole of turbine blade of heavy duty gas turbine with thermal barrier coating of double-ceramic-layer structure</title><description>The invention provides a method for processing a cooling hole of a turbine blade of a heavy duty gas turbine with a thermal barrier coating with a double-ceramic-layer structure, which comprises the following steps of: firstly, spraying the thermal barrier coating on the turbine blade by adopting a high velocity oxy-fuel spraying and atmosphere plasma spraying process by adopting a processing method of firstly coating and then punching; the thermal barrier coating structure of the second ceramic layer/the first ceramic layer/the bonding layer/the turbine blade base body is prepared; and then high-efficiency, high-quality and high-precision machining of the turbine blade air film cooling holes is achieved through the combined machining mode of long-pulse laser machining of round holes and ultrafast laser machining of forming holes, the machined cooling holes are uniform in hole diameter and good in consistency, and good industrial application prospects are achieved.
本发明提出一种带有双陶瓷层结构热障涂层的重型燃气轮机透平叶片冷却孔加工方法，通过采用"先</description><subject>APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TO SURFACES, IN GENERAL</subject><subject>CLADDING OR PLATING BY SOLDERING OR WELDING</subject><subject>COMBINED OPERATIONS</subject><subject>CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING</subject><subject>MACHINE TOOLS</subject><subject>METAL-WORKING NOT OTHERWISE PROVIDED FOR</subject><subject>OTHER WORKING OF METAL</subject><subject>PERFORMING OPERATIONS</subject><subject>PROCESSES FOR APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TOSURFACES, IN GENERAL</subject><subject>SOLDERING OR UNSOLDERING</subject><subject>SPRAYING OR ATOMISING IN GENERAL</subject><subject>TRANSPORTING</subject><subject>UNIVERSAL MACHINE TOOLS</subject><subject>WELDING</subject><subject>WORKING BY LASER BEAM</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNjD0KwkAQhdNYiHqH8QApQhRiKUGx0co-zO5OsgubnbA_Ss7gpU1ErK0efO-9b5m9rii1ccZ10FPUrKBlD5LZzkizJeAWYvLCOAJhUX2AJnyMoFIcocPw658maoiafI8WBHpvaJZhnGXTTXESlnJJHnsjc4vj1Ifok5wMtM4WLdpAm2-usu35dK8vOQ3cUBhQkqPY1LeiqMpqXx12x_KfzRu7QE2M</recordid><startdate>20240726</startdate><enddate>20240726</enddate><creator>LIU WEI</creator><creator>SHU GUOGANG</creator><creator>YU ZHIYONG</creator><creator>GUO YUWEI</creator><creator>SUN JIAN</creator><creator>LI ZHENRUI</creator><creator>MENG QINGYAN</creator><creator>LEI YUEHUA</creator><creator>YU HAIYUAN</creator><scope>EVB</scope></search><sort><creationdate>20240726</creationdate><title>Machining method for cooling hole of turbine blade of heavy duty gas turbine with thermal barrier coating of double-ceramic-layer structure</title><author>LIU WEI ; SHU GUOGANG ; YU ZHIYONG ; GUO YUWEI ; SUN JIAN ; LI ZHENRUI ; MENG QINGYAN ; LEI YUEHUA ; YU HAIYUAN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN118385894A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2024</creationdate><topic>APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TO SURFACES, IN GENERAL</topic><topic>CLADDING OR PLATING BY SOLDERING OR WELDING</topic><topic>COMBINED OPERATIONS</topic><topic>CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING</topic><topic>MACHINE TOOLS</topic><topic>METAL-WORKING NOT OTHERWISE PROVIDED FOR</topic><topic>OTHER WORKING OF METAL</topic><topic>PERFORMING OPERATIONS</topic><topic>PROCESSES FOR APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TOSURFACES, IN GENERAL</topic><topic>SOLDERING OR UNSOLDERING</topic><topic>SPRAYING OR ATOMISING IN GENERAL</topic><topic>TRANSPORTING</topic><topic>UNIVERSAL MACHINE TOOLS</topic><topic>WELDING</topic><topic>WORKING BY LASER BEAM</topic><toplevel>online_resources</toplevel><creatorcontrib>LIU WEI</creatorcontrib><creatorcontrib>SHU GUOGANG</creatorcontrib><creatorcontrib>YU ZHIYONG</creatorcontrib><creatorcontrib>GUO YUWEI</creatorcontrib><creatorcontrib>SUN JIAN</creatorcontrib><creatorcontrib>LI ZHENRUI</creatorcontrib><creatorcontrib>MENG QINGYAN</creatorcontrib><creatorcontrib>LEI YUEHUA</creatorcontrib><creatorcontrib>YU HAIYUAN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>LIU WEI</au><au>SHU GUOGANG</au><au>YU ZHIYONG</au><au>GUO YUWEI</au><au>SUN JIAN</au><au>LI ZHENRUI</au><au>MENG QINGYAN</au><au>LEI YUEHUA</au><au>YU HAIYUAN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Machining method for cooling hole of turbine blade of heavy duty gas turbine with thermal barrier coating of double-ceramic-layer structure</title><date>2024-07-26</date><risdate>2024</risdate><abstract>The invention provides a method for processing a cooling hole of a turbine blade of a heavy duty gas turbine with a thermal barrier coating with a double-ceramic-layer structure, which comprises the following steps of: firstly, spraying the thermal barrier coating on the turbine blade by adopting a high velocity oxy-fuel spraying and atmosphere plasma spraying process by adopting a processing method of firstly coating and then punching; the thermal barrier coating structure of the second ceramic layer/the first ceramic layer/the bonding layer/the turbine blade base body is prepared; and then high-efficiency, high-quality and high-precision machining of the turbine blade air film cooling holes is achieved through the combined machining mode of long-pulse laser machining of round holes and ultrafast laser machining of forming holes, the machined cooling holes are uniform in hole diameter and good in consistency, and good industrial application prospects are achieved.
本发明提出一种带有双陶瓷层结构热障涂层的重型燃气轮机透平叶片冷却孔加工方法，通过采用"先</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TO SURFACES, IN GENERAL CLADDING OR PLATING BY SOLDERING OR WELDING COMBINED OPERATIONS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING MACHINE TOOLS METAL-WORKING NOT OTHERWISE PROVIDED FOR OTHER WORKING OF METAL PERFORMING OPERATIONS PROCESSES FOR APPLYING LIQUIDS OR OTHER FLUENT MATERIALS TOSURFACES, IN GENERAL SOLDERING OR UNSOLDERING SPRAYING OR ATOMISING IN GENERAL TRANSPORTING UNIVERSAL MACHINE TOOLS WELDING WORKING BY LASER BEAM |
| title | Machining method for cooling hole of turbine blade of heavy duty gas turbine with thermal barrier coating of double-ceramic-layer structure |
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