GAS TURBINE ENGINE TURBINE COOLING SYSTEM
A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cool...
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| creator | SCANLON Timothy J MAGUIRE Alan R |
| description | A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode. |
| format | Patent |
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The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.</description><language>eng</language><subject>ACTUATING-FLOATS ; AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COCKS ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; DEVICES FOR VENTING OR AERATING ; ENGINE PLANTS IN GENERAL ; ENGINEERING ELEMENTS AND UNITS ; GAS-TURBINE PLANTS ; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; 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 ; TAPS ; THERMAL INSULATION IN GENERAL ; VALVES ; WEAPONS</subject><creationdate>2017</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=20170615&DB=EPODOC&CC=US&NR=2017167273A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25562,76317</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170615&DB=EPODOC&CC=US&NR=2017167273A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>SCANLON Timothy J</creatorcontrib><creatorcontrib>MAGUIRE Alan R</creatorcontrib><title>GAS TURBINE ENGINE TURBINE COOLING SYSTEM</title><description>A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.</description><subject>ACTUATING-FLOATS</subject><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COCKS</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>DEVICES FOR VENTING OR AERATING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>ENGINEERING ELEMENTS AND UNITS</subject><subject>GAS-TURBINE PLANTS</subject><subject>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</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>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>TAPS</subject><subject>THERMAL INSULATION IN GENERAL</subject><subject>VALVES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNB0dwxWCAkNcvL0c1Vw9XMHUTCus7-_j6efu0JwZHCIqy8PA2taYk5xKi-U5mZQdnMNcfbQTS3Ij08tLkhMTs1LLYkPDTYyMDQ3NDM3Mjd2NDQmThUAwEMlXw</recordid><startdate>20170615</startdate><enddate>20170615</enddate><creator>SCANLON Timothy J</creator><creator>MAGUIRE Alan R</creator><scope>EVB</scope></search><sort><creationdate>20170615</creationdate><title>GAS TURBINE ENGINE TURBINE COOLING SYSTEM</title><author>SCANLON Timothy J ; MAGUIRE Alan R</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2017167273A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2017</creationdate><topic>ACTUATING-FLOATS</topic><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COCKS</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>DEVICES FOR VENTING OR AERATING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>ENGINEERING ELEMENTS AND UNITS</topic><topic>GAS-TURBINE PLANTS</topic><topic>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</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>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>TAPS</topic><topic>THERMAL INSULATION IN GENERAL</topic><topic>VALVES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>SCANLON Timothy J</creatorcontrib><creatorcontrib>MAGUIRE Alan R</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SCANLON Timothy J</au><au>MAGUIRE Alan R</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>GAS TURBINE ENGINE TURBINE COOLING SYSTEM</title><date>2017-06-15</date><risdate>2017</risdate><abstract>A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | ACTUATING-FLOATS AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COCKS COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DEVICES FOR VENTING OR AERATING ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS 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 TAPS THERMAL INSULATION IN GENERAL VALVES WEAPONS |
| title | GAS TURBINE ENGINE TURBINE COOLING SYSTEM |
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