COOLING CIRCUIT FOR MULTI-WALL BLADE
PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the t...
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| creator | CHARLES PERRY JACOB II WEBER DAVID WAYNE MEHMET SULEYMAN CIRAY |
| description | PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; where the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.SELECTED DRAWING: Figure 1
【課題】多重壁タービンブレード冷却回路の圧力損失を低減させること。【解決手段】一実施形態によるタービンブレード冷却システムは、タービンブレードの第１のチャンネルを通じて流れる第１のガス流をタービンブレードの中央プレナムの中へ向きを変えるための第１のターンと、タービンブレードの第２のチャンネルを通じて流れる第２のガス流を中央プレナムの中へ向きを変えるための第２のターンとを備え、中央プレナムにおける第１のガス流と第２のガス流の衝突を低減するように第１のターンは第２のターンからずれている。【選択図】図１ |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_JP2017115885A</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>JP2017115885A</sourcerecordid><originalsourceid>FETCH-epo_espacenet_JP2017115885A3</originalsourceid><addsrcrecordid>eNrjZFBx9vf38fRzV3D2DHIO9QxRcPMPUvAN9Qnx1A139PFRcPJxdHHlYWBNS8wpTuWF0twMSm6uIc4euqkF-fGpxQWJyal5qSXxXgFGBobmhoamFhamjsZEKQIAsoIjUA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>COOLING CIRCUIT FOR MULTI-WALL BLADE</title><source>esp@cenet</source><creator>CHARLES PERRY JACOB II ; WEBER DAVID WAYNE ; MEHMET SULEYMAN CIRAY</creator><creatorcontrib>CHARLES PERRY JACOB II ; WEBER DAVID WAYNE ; MEHMET SULEYMAN CIRAY</creatorcontrib><description>PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; where the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.SELECTED DRAWING: Figure 1
【課題】多重壁タービンブレード冷却回路の圧力損失を低減させること。【解決手段】一実施形態によるタービンブレード冷却システムは、タービンブレードの第１のチャンネルを通じて流れる第１のガス流をタービンブレードの中央プレナムの中へ向きを変えるための第１のターンと、タービンブレードの第２のチャンネルを通じて流れる第２のガス流を中央プレナムの中へ向きを変えるための第２のターンとを備え、中央プレナムにおける第１のガス流と第２のガス流の衝突を低減するように第１のターンは第２のターンからずれている。【選択図】図１</description><language>eng ; jpn</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINE PLANTS IN GENERAL ; GAS-TURBINE PLANTS ; 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 ; 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=20170629&DB=EPODOC&CC=JP&NR=2017115885A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25562,76317</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170629&DB=EPODOC&CC=JP&NR=2017115885A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>CHARLES PERRY JACOB II</creatorcontrib><creatorcontrib>WEBER DAVID WAYNE</creatorcontrib><creatorcontrib>MEHMET SULEYMAN CIRAY</creatorcontrib><title>COOLING CIRCUIT FOR MULTI-WALL BLADE</title><description>PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; where the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.SELECTED DRAWING: Figure 1
【課題】多重壁タービンブレード冷却回路の圧力損失を低減させること。【解決手段】一実施形態によるタービンブレード冷却システムは、タービンブレードの第１のチャンネルを通じて流れる第１のガス流をタービンブレードの中央プレナムの中へ向きを変えるための第１のターンと、タービンブレードの第２のチャンネルを通じて流れる第２のガス流を中央プレナムの中へ向きを変えるための第２のターンとを備え、中央プレナムにおける第１のガス流と第２のガス流の衝突を低減するように第１のターンは第２のターンからずれている。【選択図】図１</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>ENGINE PLANTS IN GENERAL</subject><subject>GAS-TURBINE PLANTS</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>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFBx9vf38fRzV3D2DHIO9QxRcPMPUvAN9Qnx1A139PFRcPJxdHHlYWBNS8wpTuWF0twMSm6uIc4euqkF-fGpxQWJyal5qSXxXgFGBobmhoamFhamjsZEKQIAsoIjUA</recordid><startdate>20170629</startdate><enddate>20170629</enddate><creator>CHARLES PERRY JACOB II</creator><creator>WEBER DAVID WAYNE</creator><creator>MEHMET SULEYMAN CIRAY</creator><scope>EVB</scope></search><sort><creationdate>20170629</creationdate><title>COOLING CIRCUIT FOR MULTI-WALL BLADE</title><author>CHARLES PERRY JACOB II ; WEBER DAVID WAYNE ; MEHMET SULEYMAN CIRAY</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2017115885A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; jpn</language><creationdate>2017</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>ENGINE PLANTS IN GENERAL</topic><topic>GAS-TURBINE PLANTS</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>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>CHARLES PERRY JACOB II</creatorcontrib><creatorcontrib>WEBER DAVID WAYNE</creatorcontrib><creatorcontrib>MEHMET SULEYMAN CIRAY</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>CHARLES PERRY JACOB II</au><au>WEBER DAVID WAYNE</au><au>MEHMET SULEYMAN CIRAY</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>COOLING CIRCUIT FOR MULTI-WALL BLADE</title><date>2017-06-29</date><risdate>2017</risdate><abstract>PROBLEM TO BE SOLVED: To reduce pressure loss in a multi-wall turbine blade cooling circuit.SOLUTION: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; where the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.SELECTED DRAWING: Figure 1
【課題】多重壁タービンブレード冷却回路の圧力損失を低減させること。【解決手段】一実施形態によるタービンブレード冷却システムは、タービンブレードの第１のチャンネルを通じて流れる第１のガス流をタービンブレードの中央プレナムの中へ向きを変えるための第１のターンと、タービンブレードの第２のチャンネルを通じて流れる第２のガス流を中央プレナムの中へ向きを変えるための第２のターンとを備え、中央プレナムにおける第１のガス流と第２のガス流の衝突を低減するように第１のターンは第２のターンからずれている。【選択図】図１</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS 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 WEAPONS |
| title | COOLING CIRCUIT FOR MULTI-WALL BLADE |
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