COOLING CIRCUIT FOR A TURBOMACHINE COMPONENT
The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoi...
Gespeichert in:
| Hauptverfasser: | , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | Jasper, Martin James Agudo, Jan Emeric |
| description | The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2021301666A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2021301666A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2021301666A13</originalsourceid><addsrcrecordid>eNrjZNBx9vf38fRzV3D2DHIO9QxRcPMPUnBUCAkNcvL3dXT28PRzVXD29w3w93P1C-FhYE1LzClO5YXS3AzKbq4hzh66qQX58anFBYnJqXmpJfGhwUYGRobGBoZmZmaOhsbEqQIAKwYmFw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>COOLING CIRCUIT FOR A TURBOMACHINE COMPONENT</title><source>esp@cenet</source><creator>Jasper, Martin James ; Agudo, Jan Emeric</creator><creatorcontrib>Jasper, Martin James ; Agudo, Jan Emeric</creatorcontrib><description>The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface.</description><language>eng</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>2021</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=20210930&DB=EPODOC&CC=US&NR=2021301666A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20210930&DB=EPODOC&CC=US&NR=2021301666A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Jasper, Martin James</creatorcontrib><creatorcontrib>Agudo, Jan Emeric</creatorcontrib><title>COOLING CIRCUIT FOR A TURBOMACHINE COMPONENT</title><description>The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface.</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>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNBx9vf38fRzV3D2DHIO9QxRcPMPUnBUCAkNcvL3dXT28PRzVXD29w3w93P1C-FhYE1LzClO5YXS3AzKbq4hzh66qQX58anFBYnJqXmpJfGhwUYGRobGBoZmZmaOhsbEqQIAKwYmFw</recordid><startdate>20210930</startdate><enddate>20210930</enddate><creator>Jasper, Martin James</creator><creator>Agudo, Jan Emeric</creator><scope>EVB</scope></search><sort><creationdate>20210930</creationdate><title>COOLING CIRCUIT FOR A TURBOMACHINE COMPONENT</title><author>Jasper, Martin James ; Agudo, Jan Emeric</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2021301666A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2021</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>Jasper, Martin James</creatorcontrib><creatorcontrib>Agudo, Jan Emeric</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Jasper, Martin James</au><au>Agudo, Jan Emeric</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>COOLING CIRCUIT FOR A TURBOMACHINE COMPONENT</title><date>2021-09-30</date><risdate>2021</risdate><abstract>The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US2021301666A1 |
| source | esp@cenet |
| 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 A TURBOMACHINE COMPONENT |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-07T00%3A35%3A53IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=Jasper,%20Martin%20James&rft.date=2021-09-30&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS2021301666A1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |