Fuel flow tuning for a stage of a gas turbine engine
A method and system for controlling combustion in a gas turbine engine (10) includes reducing an overall fuel flow provided to a stage (22) of burners (e.g. 34, 35) of the gas turbine engine until reaching a predetermined dynamic operating condition of the first burner of the stage. The method also...
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| creator | BLAND ROBERT J |
| description | A method and system for controlling combustion in a gas turbine engine (10) includes reducing an overall fuel flow provided to a stage (22) of burners (e.g. 34, 35) of the gas turbine engine until reaching a predetermined dynamic operating condition of the first burner of the stage. The method also includes maintaining, while continuing to reduce the overall fuel flow (e.g. 30), a first portion (e.g. 36), of the overall fuel flow delivered to the first burner at a maintenance level so that the predetermined dynamic operating condition of the first burner is maintained. |
| format | Patent |
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The method also includes maintaining, while continuing to reduce the overall fuel flow (e.g. 30), a first portion (e.g. 36), of the overall fuel flow delivered to the first burner at a maintenance level so that the predetermined dynamic operating condition of the first burner is maintained.</description><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>2010</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=20101005&DB=EPODOC&CC=US&NR=7805922B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20101005&DB=EPODOC&CC=US&NR=7805922B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BLAND ROBERT J</creatorcontrib><title>Fuel flow tuning for a stage of a gas turbine engine</title><description>A method and system for controlling combustion in a gas turbine engine (10) includes reducing an overall fuel flow provided to a stage (22) of burners (e.g. 34, 35) of the gas turbine engine until reaching a predetermined dynamic operating condition of the first burner of the stage. The method also includes maintaining, while continuing to reduce the overall fuel flow (e.g. 30), a first portion (e.g. 36), of the overall fuel flow delivered to the first burner at a maintenance level so that the predetermined dynamic operating condition of the first burner is maintained.</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>2010</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDBxK03NUUjLyS9XKCnNy8xLV0jLL1JIVCguSUxPVchPAzLTE4uBckVJmXmpCql56UCKh4E1LTGnOJUXSnMzKLi5hjh76KYW5MenFhckJqfmpZbEhwabWxiYWhoZORkZE6EEAHMsK6Q</recordid><startdate>20101005</startdate><enddate>20101005</enddate><creator>BLAND ROBERT J</creator><scope>EVB</scope></search><sort><creationdate>20101005</creationdate><title>Fuel flow tuning for a stage of a gas turbine engine</title><author>BLAND ROBERT J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US7805922B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2010</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>BLAND ROBERT J</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BLAND ROBERT J</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Fuel flow tuning for a stage of a gas turbine engine</title><date>2010-10-05</date><risdate>2010</risdate><abstract>A method and system for controlling combustion in a gas turbine engine (10) includes reducing an overall fuel flow provided to a stage (22) of burners (e.g. 34, 35) of the gas turbine engine until reaching a predetermined dynamic operating condition of the first burner of the stage. The method also includes maintaining, while continuing to reduce the overall fuel flow (e.g. 30), a first portion (e.g. 36), of the overall fuel flow delivered to the first burner at a maintenance level so that the predetermined dynamic operating condition of the first burner is maintained.</abstract><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 | Fuel flow tuning for a stage of a gas turbine engine |
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