GAS TURBINE SYSTEM AND OPERATION METHOD FOR THE SAME
PROBLEM TO BE SOLVED: To provide a gas turbine system capable of being switched to an optimum combustion mode according to a variation in the actual temperature of combustion gas at the inlet of a gas turbine even if an abrupt change in the operating condition of the gas turbine occurs, and an opera...
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| creator | DEJIMA MASARU TOUBOU MASAYUKI |
| description | PROBLEM TO BE SOLVED: To provide a gas turbine system capable of being switched to an optimum combustion mode according to a variation in the actual temperature of combustion gas at the inlet of a gas turbine even if an abrupt change in the operating condition of the gas turbine occurs, and an operation method for the same. SOLUTION: This gas turbine system comprises a combustion gas temperature calculation part 11 for abrupt change installed separately from a combustion gas temperature calculation part 134 and calculating the temperature of the combustion gas at the inlet of the gas turbine by using a fuel flow rate instructive value 125 and an abrupt change operation detection part 10 detecting the occurrence of the abrupt change of the operating state of the gas turbine 12. When the abrupt change occurs, the rate of the fuel flow rate fed to a premixed combustor and a diffuse combustor is calculated by using the result of the calculation of the temperature of the combustion gas at the inlet of the gas turbine calculated by the combustion gas temperature calculation part 11 for abrupt change. COPYRIGHT: (C)2004,JPO |
| format | Patent |
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SOLUTION: This gas turbine system comprises a combustion gas temperature calculation part 11 for abrupt change installed separately from a combustion gas temperature calculation part 134 and calculating the temperature of the combustion gas at the inlet of the gas turbine by using a fuel flow rate instructive value 125 and an abrupt change operation detection part 10 detecting the occurrence of the abrupt change of the operating state of the gas turbine 12. When the abrupt change occurs, the rate of the fuel flow rate fed to a premixed combustor and a diffuse combustor is calculated by using the result of the calculation of the temperature of the combustion gas at the inlet of the gas turbine calculated by the combustion gas temperature calculation part 11 for abrupt change. COPYRIGHT: (C)2004,JPO</description><edition>7</edition><language>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>2004</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=20040408&DB=EPODOC&CC=JP&NR=2004108315A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76418</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20040408&DB=EPODOC&CC=JP&NR=2004108315A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>DEJIMA MASARU</creatorcontrib><creatorcontrib>TOUBOU MASAYUKI</creatorcontrib><title>GAS TURBINE SYSTEM AND OPERATION METHOD FOR THE SAME</title><description>PROBLEM TO BE SOLVED: To provide a gas turbine system capable of being switched to an optimum combustion mode according to a variation in the actual temperature of combustion gas at the inlet of a gas turbine even if an abrupt change in the operating condition of the gas turbine occurs, and an operation method for the same. SOLUTION: This gas turbine system comprises a combustion gas temperature calculation part 11 for abrupt change installed separately from a combustion gas temperature calculation part 134 and calculating the temperature of the combustion gas at the inlet of the gas turbine by using a fuel flow rate instructive value 125 and an abrupt change operation detection part 10 detecting the occurrence of the abrupt change of the operating state of the gas turbine 12. When the abrupt change occurs, the rate of the fuel flow rate fed to a premixed combustor and a diffuse combustor is calculated by using the result of the calculation of the temperature of the combustion gas at the inlet of the gas turbine calculated by the combustion gas temperature calculation part 11 for abrupt change. COPYRIGHT: (C)2004,JPO</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>GAS-TURBINE PLANTS</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>2004</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDBxdwxWCAkNcvL0c1UIjgwOcfVVcPRzUfAPcA1yDPH091PwdQ3x8HdRcPMPUgjxAKpx9HXlYWBNS8wpTuWF0twMSm6uIc4euqkF-fGpxQWJyal5qSXxXgFGBgYmhgYWxoamjsZEKQIA_foniw</recordid><startdate>20040408</startdate><enddate>20040408</enddate><creator>DEJIMA MASARU</creator><creator>TOUBOU MASAYUKI</creator><scope>EVB</scope></search><sort><creationdate>20040408</creationdate><title>GAS TURBINE SYSTEM AND OPERATION METHOD FOR THE SAME</title><author>DEJIMA MASARU ; TOUBOU MASAYUKI</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2004108315A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2004</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>GAS-TURBINE PLANTS</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>DEJIMA MASARU</creatorcontrib><creatorcontrib>TOUBOU MASAYUKI</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>DEJIMA MASARU</au><au>TOUBOU MASAYUKI</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE SYSTEM AND OPERATION METHOD FOR THE SAME</title><date>2004-04-08</date><risdate>2004</risdate><abstract>PROBLEM TO BE SOLVED: To provide a gas turbine system capable of being switched to an optimum combustion mode according to a variation in the actual temperature of combustion gas at the inlet of a gas turbine even if an abrupt change in the operating condition of the gas turbine occurs, and an operation method for the same. SOLUTION: This gas turbine system comprises a combustion gas temperature calculation part 11 for abrupt change installed separately from a combustion gas temperature calculation part 134 and calculating the temperature of the combustion gas at the inlet of the gas turbine by using a fuel flow rate instructive value 125 and an abrupt change operation detection part 10 detecting the occurrence of the abrupt change of the operating state of the gas turbine 12. When the abrupt change occurs, the rate of the fuel flow rate fed to a premixed combustor and a diffuse combustor is calculated by using the result of the calculation of the temperature of the combustion gas at the inlet of the gas turbine calculated by the combustion gas temperature calculation part 11 for abrupt change. COPYRIGHT: (C)2004,JPO</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
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| language | 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 | GAS TURBINE SYSTEM AND OPERATION METHOD FOR THE SAME |
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