Turbine blade internal cooling configuration
A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the co...
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| creator | PINERO SANDRA S YEE STEPHEN J DUBE BRYAN P PIETRASZKIEWICZ EDWARD F LEVY RYAN SHEPARD VALERIO DOMENICO HARTMANN SCOTT D HASSAN MOHAMED |
| description | A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit. |
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The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.</description><language>eng</language><subject>BLASTING ; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ; ENGINE PLANTS IN GENERAL ; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC ; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS ; HEATING ; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS ; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS ; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE ; WEAPONS</subject><creationdate>2009</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=20091119&DB=EPODOC&CC=US&NR=2009285684A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20091119&DB=EPODOC&CC=US&NR=2009285684A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>PINERO SANDRA S</creatorcontrib><creatorcontrib>YEE STEPHEN J</creatorcontrib><creatorcontrib>DUBE BRYAN P</creatorcontrib><creatorcontrib>PIETRASZKIEWICZ EDWARD F</creatorcontrib><creatorcontrib>LEVY RYAN SHEPARD</creatorcontrib><creatorcontrib>VALERIO DOMENICO</creatorcontrib><creatorcontrib>HARTMANN SCOTT D</creatorcontrib><creatorcontrib>HASSAN MOHAMED</creatorcontrib><title>Turbine blade internal cooling configuration</title><description>A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.</description><subject>BLASTING</subject><subject>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</subject><subject>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</subject><subject>HEATING</subject><subject>INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS</subject><subject>INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04</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>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</subject><subject>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2009</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNAJKS1KysxLVUjKSUxJVcjMK0ktykvMUUjOz8_JzEsH0nlpmemlRYklmfl5PAysaYk5xam8UJqbQdnNNcTZQze1ID8-tbggMTk1L7UkPjTYyMDA0sjC1MzCxNHQmDhVAGIzKzA</recordid><startdate>20091119</startdate><enddate>20091119</enddate><creator>PINERO SANDRA S</creator><creator>YEE STEPHEN J</creator><creator>DUBE BRYAN P</creator><creator>PIETRASZKIEWICZ EDWARD F</creator><creator>LEVY RYAN SHEPARD</creator><creator>VALERIO DOMENICO</creator><creator>HARTMANN SCOTT D</creator><creator>HASSAN MOHAMED</creator><scope>EVB</scope></search><sort><creationdate>20091119</creationdate><title>Turbine blade internal cooling configuration</title><author>PINERO SANDRA S ; YEE STEPHEN J ; DUBE BRYAN P ; PIETRASZKIEWICZ EDWARD F ; LEVY RYAN SHEPARD ; VALERIO DOMENICO ; HARTMANN SCOTT D ; HASSAN MOHAMED</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2009285684A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2009</creationdate><topic>BLASTING</topic><topic>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</topic><topic>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</topic><topic>HEATING</topic><topic>INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS</topic><topic>INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04</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>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</topic><topic>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>PINERO SANDRA S</creatorcontrib><creatorcontrib>YEE STEPHEN J</creatorcontrib><creatorcontrib>DUBE BRYAN P</creatorcontrib><creatorcontrib>PIETRASZKIEWICZ EDWARD F</creatorcontrib><creatorcontrib>LEVY RYAN SHEPARD</creatorcontrib><creatorcontrib>VALERIO DOMENICO</creatorcontrib><creatorcontrib>HARTMANN SCOTT D</creatorcontrib><creatorcontrib>HASSAN MOHAMED</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>PINERO SANDRA S</au><au>YEE STEPHEN J</au><au>DUBE BRYAN P</au><au>PIETRASZKIEWICZ EDWARD F</au><au>LEVY RYAN SHEPARD</au><au>VALERIO DOMENICO</au><au>HARTMANN SCOTT D</au><au>HASSAN MOHAMED</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Turbine blade internal cooling configuration</title><date>2009-11-19</date><risdate>2009</risdate><abstract>A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS |
| title | Turbine blade internal cooling configuration |
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