Turbomachine Rotor Blade Cooling Passage
The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of...
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| creator | Jones, Mark Andrew |
| description | The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core. |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2018340428A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2018340428A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2018340428A13</originalsourceid><addsrcrecordid>eNrjZNAIKS1Kys9NTM7IzEtVCMovyS9ScMpJTElVcM7Pz8nMS1cISCwuTkxP5WFgTUvMKU7lhdLcDMpuriHOHrqpBfnxqcUFicmpeakl8aHBRgaGFsYmBiZGFo6GxsSpAgBOUyjh</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Turbomachine Rotor Blade Cooling Passage</title><source>esp@cenet</source><creator>Jones, Mark Andrew</creator><creatorcontrib>Jones, Mark Andrew</creatorcontrib><description>The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.</description><language>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>2018</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=20181129&DB=EPODOC&CC=US&NR=2018340428A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,777,882,25545,76296</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20181129&DB=EPODOC&CC=US&NR=2018340428A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Jones, Mark Andrew</creatorcontrib><title>Turbomachine Rotor Blade Cooling Passage</title><description>The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.</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>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNAIKS1Kys9NTM7IzEtVCMovyS9ScMpJTElVcM7Pz8nMS1cISCwuTkxP5WFgTUvMKU7lhdLcDMpuriHOHrqpBfnxqcUFicmpeakl8aHBRgaGFsYmBiZGFo6GxsSpAgBOUyjh</recordid><startdate>20181129</startdate><enddate>20181129</enddate><creator>Jones, Mark Andrew</creator><scope>EVB</scope></search><sort><creationdate>20181129</creationdate><title>Turbomachine Rotor Blade Cooling Passage</title><author>Jones, Mark Andrew</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2018340428A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2018</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>Jones, Mark Andrew</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Jones, Mark Andrew</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Turbomachine Rotor Blade Cooling Passage</title><date>2018-11-29</date><risdate>2018</risdate><abstract>The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.</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 | Turbomachine Rotor Blade Cooling Passage |
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