GAS TURBINE COMBUSTOR
PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a flow sleeve structure improved in vibration-resisting performance.SOLUTION: A gas turbine combustor includes a liner 5, a transition piece 4, and a flow sleeve 7 composed of a plurality of split pieces integrated by welding a tie p...
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| creator | ICHIKAWA KUNIHIRO SEKIHARA TAKASHI |
| description | PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a flow sleeve structure improved in vibration-resisting performance.SOLUTION: A gas turbine combustor includes a liner 5, a transition piece 4, and a flow sleeve 7 composed of a plurality of split pieces integrated by welding a tie piece 8 along their butting portions. The tie piece is continuously extended along the longitudinal direction of the butting portions of the split pieces, and composed of a first member 81 disposed to cover the butting portions, and a second member 82 formed on an end portion of the first member, being wider than the first member, and having a cutout portion 10. |
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The tie piece is continuously extended along the longitudinal direction of the butting portions of the split pieces, and composed of a first member 81 disposed to cover the butting portions, and a second member 82 formed on an end portion of the first member, being wider than the first member, and having a cutout portion 10.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2014</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=20140609&DB=EPODOC&CC=JP&NR=2014105983A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20140609&DB=EPODOC&CC=JP&NR=2014105983A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>ICHIKAWA KUNIHIRO</creatorcontrib><creatorcontrib>SEKIHARA TAKASHI</creatorcontrib><title>GAS TURBINE COMBUSTOR</title><description>PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a flow sleeve structure improved in vibration-resisting performance.SOLUTION: A gas turbine combustor includes a liner 5, a transition piece 4, and a flow sleeve 7 composed of a plurality of split pieces integrated by welding a tie piece 8 along their butting portions. The tie piece is continuously extended along the longitudinal direction of the butting portions of the split pieces, and composed of a first member 81 disposed to cover the butting portions, and a second member 82 formed on an end portion of the first member, being wider than the first member, and having a cutout portion 10.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION ENGINES</subject><subject>COMBUSTION PROCESSES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2014</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBB1dwxWCAkNcvL0c1Vw9vd1Cg0O8Q_iYWBNS8wpTuWF0twMSm6uIc4euqkF-fGpxQWJyal5qSXxXgFGBoYmhgamlhbGjsZEKQIA2H4fZA</recordid><startdate>20140609</startdate><enddate>20140609</enddate><creator>ICHIKAWA KUNIHIRO</creator><creator>SEKIHARA TAKASHI</creator><scope>EVB</scope></search><sort><creationdate>20140609</creationdate><title>GAS TURBINE COMBUSTOR</title><author>ICHIKAWA KUNIHIRO ; SEKIHARA TAKASHI</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2014105983A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2014</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION ENGINES</topic><topic>COMBUSTION PROCESSES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>ICHIKAWA KUNIHIRO</creatorcontrib><creatorcontrib>SEKIHARA TAKASHI</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>ICHIKAWA KUNIHIRO</au><au>SEKIHARA TAKASHI</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE COMBUSTOR</title><date>2014-06-09</date><risdate>2014</risdate><abstract>PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a flow sleeve structure improved in vibration-resisting performance.SOLUTION: A gas turbine combustor includes a liner 5, a transition piece 4, and a flow sleeve 7 composed of a plurality of split pieces integrated by welding a tie piece 8 along their butting portions. The tie piece is continuously extended along the longitudinal direction of the butting portions of the split pieces, and composed of a first member 81 disposed to cover the butting portions, and a second member 82 formed on an end portion of the first member, being wider than the first member, and having a cutout portion 10.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | GAS TURBINE COMBUSTOR |
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