TURBINE ROTOR BLADE WITH AIRFOIL COOLING INTEGRATED WITH IMPINGEMENT PLATFORM COOLING
An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting t...
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| creator | WAYWOOD ANTHONY KOESTER STEVEN LEE CHING-PANG |
| description | An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined atleast partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radiallyoutboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50),before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c). The impinged area (60) may include a turbulator (70) to enhance heat transfer.
本发明涉及用于涡轮机转子叶片（10）的集成式翼型部和平台冷却系统（30），其包括多个蜿蜒的冷却支腿（32a、32c、42a、42c），冷却支腿（3 |
| format | Patent |
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本发明涉及用于涡轮机转子叶片（10）的集成式翼型部和平台冷却系统（30），其包括多个蜿蜒的冷却支腿（32a、32c、42a、42c），冷却支腿（3</description><language>chi ; eng</language><subject>BLASTING ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2019</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=20191122&DB=EPODOC&CC=CN&NR=110494628A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20191122&DB=EPODOC&CC=CN&NR=110494628A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>WAYWOOD ANTHONY</creatorcontrib><creatorcontrib>KOESTER STEVEN</creatorcontrib><creatorcontrib>LEE CHING-PANG</creatorcontrib><title>TURBINE ROTOR BLADE WITH AIRFOIL COOLING INTEGRATED WITH IMPINGEMENT PLATFORM COOLING</title><description>An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined atleast partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radiallyoutboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50),before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c). The impinged area (60) may include a turbulator (70) to enhance heat transfer.
本发明涉及用于涡轮机转子叶片（10）的集成式翼型部和平台冷却系统（30），其包括多个蜿蜒的冷却支腿（32a、32c、42a、42c），冷却支腿（3</description><subject>BLASTING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</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>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZAgNCQ1y8vRzVQjyD_EPUnDycXRxVQj3DPFQcPQMcvP39FFw9vf38fRzV_D0C3F1D3IMcXWByHv6BgCFXX1d_UIUAnwcQ9z8g3xhinkYWNMSc4pTeaE0N4Oim2uIs4duakF-fGpxQWJyal5qSbyzn6GhgYmliZmRhaMxMWoAePQwpg</recordid><startdate>20191122</startdate><enddate>20191122</enddate><creator>WAYWOOD ANTHONY</creator><creator>KOESTER STEVEN</creator><creator>LEE CHING-PANG</creator><scope>EVB</scope></search><sort><creationdate>20191122</creationdate><title>TURBINE ROTOR BLADE WITH AIRFOIL COOLING INTEGRATED WITH IMPINGEMENT PLATFORM COOLING</title><author>WAYWOOD ANTHONY ; KOESTER STEVEN ; LEE CHING-PANG</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN110494628A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2019</creationdate><topic>BLASTING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</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>WAYWOOD ANTHONY</creatorcontrib><creatorcontrib>KOESTER STEVEN</creatorcontrib><creatorcontrib>LEE CHING-PANG</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>WAYWOOD ANTHONY</au><au>KOESTER STEVEN</au><au>LEE CHING-PANG</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBINE ROTOR BLADE WITH AIRFOIL COOLING INTEGRATED WITH IMPINGEMENT PLATFORM COOLING</title><date>2019-11-22</date><risdate>2019</risdate><abstract>An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined atleast partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radiallyoutboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50),before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c). The impinged area (60) may include a turbulator (70) to enhance heat transfer.
本发明涉及用于涡轮机转子叶片（10）的集成式翼型部和平台冷却系统（30），其包括多个蜿蜒的冷却支腿（32a、32c、42a、42c），冷却支腿（3</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | TURBINE ROTOR BLADE WITH AIRFOIL COOLING INTEGRATED WITH IMPINGEMENT PLATFORM COOLING |
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