Optimization method for flame tube of combustion chamber of gas turbine impacting cooling system
The invention relates to the field of optimization of flame tube of a combustion chamber of a gas turbine impacting cooling system, aims to solve the problem that an existing impacting structure is difficult to optimize when the cooling design cannot meet the wall temperature requirement, and provid...
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| creator | TIAN XIAOJING YANG ANJIAN HUANG YI LIU WEIBING ZHANG YUAN FENG ZHENZHEN FENG YUNXIAN |
| description | The invention relates to the field of optimization of flame tube of a combustion chamber of a gas turbine impacting cooling system, aims to solve the problem that an existing impacting structure is difficult to optimize when the cooling design cannot meet the wall temperature requirement, and provides an optimization method for flame tube of the combustion chamber of the gas turbine impacting cooling system. The optimization method comprises the following steps that 1), initial measurement is carried out, specifically, the wall temperature measurement is carried out on the original combustionchamber to obtain a temperature value Ti corresponding to each row of cooling holes of the wall surface, and a value of the depth ratio Y% of an impact jet flow corresponding to each row of the cooling holes is calculated through an equation; and 2), structural optimization is carried out, specifically, aiming at parts where the measured temperature values Ti are larger than or equal to limit temperature values Tm, namely |
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The optimization method comprises the following steps that 1), initial measurement is carried out, specifically, the wall temperature measurement is carried out on the original combustionchamber to obtain a temperature value Ti corresponding to each row of cooling holes of the wall surface, and a value of the depth ratio Y% of an impact jet flow corresponding to each row of the cooling holes is calculated through an equation; and 2), structural optimization is carried out, specifically, aiming at parts where the measured temperature values Ti are larger than or equal to limit temperature values Tm, namely</description><language>chi ; eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; 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=20200228&DB=EPODOC&CC=CN&NR=110848030A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20200228&DB=EPODOC&CC=CN&NR=110848030A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>TIAN XIAOJING</creatorcontrib><creatorcontrib>YANG ANJIAN</creatorcontrib><creatorcontrib>HUANG YI</creatorcontrib><creatorcontrib>LIU WEIBING</creatorcontrib><creatorcontrib>ZHANG YUAN</creatorcontrib><creatorcontrib>FENG ZHENZHEN</creatorcontrib><creatorcontrib>FENG YUNXIAN</creatorcontrib><title>Optimization method for flame tube of combustion chamber of gas turbine impacting cooling system</title><description>The invention relates to the field of optimization of flame tube of a combustion chamber of a gas turbine impacting cooling system, aims to solve the problem that an existing impacting structure is difficult to optimize when the cooling design cannot meet the wall temperature requirement, and provides an optimization method for flame tube of the combustion chamber of the gas turbine impacting cooling system. 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The optimization method comprises the following steps that 1), initial measurement is carried out, specifically, the wall temperature measurement is carried out on the original combustionchamber to obtain a temperature value Ti corresponding to each row of cooling holes of the wall surface, and a value of the depth ratio Y% of an impact jet flow corresponding to each row of the cooling holes is calculated through an equation; and 2), structural optimization is carried out, specifically, aiming at parts where the measured temperature values Ti are larger than or equal to limit temperature values Tm, namely</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Optimization method for flame tube of combustion chamber of gas turbine impacting cooling system |
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