GAS TURBINE BLADE AND GAS TURBINE EQUIPPED THEREWITH
PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream...
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| creator | YURI MASANORI HANEDA SATORU |
| description | PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream side. A first wall 22A and a third wall 22C are disposed so that a space therebetween is gradually wider from the belly side toward the back side of the blade. A second wall 24B extends approximately parallel to the first wall 22A. A second flow path 12B having an approximately square cross section is formed of the first wall 22A, a back sidewall 4B of the blade, the second wall 24B and a belly sidewall 4A of the blade. A third flow path 12C having an approximately triangular cross section is formed of the second wall 24B, the belly sidewall 4A of the blade and the third wall 22C. |
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A first wall 22A and a third wall 22C are disposed so that a space therebetween is gradually wider from the belly side toward the back side of the blade. A second wall 24B extends approximately parallel to the first wall 22A. A second flow path 12B having an approximately square cross section is formed of the first wall 22A, a back sidewall 4B of the blade, the second wall 24B and a belly sidewall 4A of the blade. A third flow path 12C having an approximately triangular cross section is formed of the second wall 24B, the belly sidewall 4A of the blade and the third wall 22C.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINE PLANTS IN GENERAL ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2012</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=20120913&DB=EPODOC&CC=JP&NR=2012177377A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20120913&DB=EPODOC&CC=JP&NR=2012177377A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>YURI MASANORI</creatorcontrib><creatorcontrib>HANEDA SATORU</creatorcontrib><title>GAS TURBINE BLADE AND GAS TURBINE EQUIPPED THEREWITH</title><description>PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream side. A first wall 22A and a third wall 22C are disposed so that a space therebetween is gradually wider from the belly side toward the back side of the blade. A second wall 24B extends approximately parallel to the first wall 22A. A second flow path 12B having an approximately square cross section is formed of the first wall 22A, a back sidewall 4B of the blade, the second wall 24B and a belly sidewall 4A of the blade. A third flow path 12C having an approximately triangular cross section is formed of the second wall 24B, the belly sidewall 4A of the blade and the third wall 22C.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</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>2012</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDBxdwxWCAkNcvL0c1Vw8nF0cVVw9HNRQBZ1DQz1DAhwdVEI8XANcg33DPHgYWBNS8wpTuWF0twMSm6uIc4euqkF-fGpxQWJyal5qSXxXgFGBoZGhubmxubmjsZEKQIA8YQnnQ</recordid><startdate>20120913</startdate><enddate>20120913</enddate><creator>YURI MASANORI</creator><creator>HANEDA SATORU</creator><scope>EVB</scope></search><sort><creationdate>20120913</creationdate><title>GAS TURBINE BLADE AND GAS TURBINE EQUIPPED THEREWITH</title><author>YURI MASANORI ; HANEDA SATORU</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2012177377A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2012</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</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>YURI MASANORI</creatorcontrib><creatorcontrib>HANEDA SATORU</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>YURI MASANORI</au><au>HANEDA SATORU</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE BLADE AND GAS TURBINE EQUIPPED THEREWITH</title><date>2012-09-13</date><risdate>2012</risdate><abstract>PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream side. A first wall 22A and a third wall 22C are disposed so that a space therebetween is gradually wider from the belly side toward the back side of the blade. A second wall 24B extends approximately parallel to the first wall 22A. A second flow path 12B having an approximately square cross section is formed of the first wall 22A, a back sidewall 4B of the blade, the second wall 24B and a belly sidewall 4A of the blade. A third flow path 12C having an approximately triangular cross section is formed of the second wall 24B, the belly sidewall 4A of the blade and the third wall 22C.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | GAS TURBINE BLADE AND GAS TURBINE EQUIPPED THEREWITH |
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