Gas turbine engines with improved leading edge airfoil cooling
An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall...
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 | Malak, Malak Fouad Narayanan, Sridharan Reghupathy Jayamurugan, Chandiran Paramanandam, Karthikeyan Srinivasan, Balamurugan |
| description | An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US10934856B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US10934856B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US10934856B23</originalsourceid><addsrcrecordid>eNrjZLBzTyxWKCktSsrMS1VIzUsHUsUK5ZklGQqZuQVF-WWpKQo5qYkpmXnpCqkp6akKiZlFafmZOQrJ-fk5QEEeBta0xJziVF4ozc2g6OYa4uyhm1qQH59aXJCYnJqXWhIfGmxoYGlsYmFq5mRkTIwaAFcjMLo</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Gas turbine engines with improved leading edge airfoil cooling</title><source>esp@cenet</source><creator>Malak, Malak Fouad ; Narayanan, Sridharan Reghupathy ; Jayamurugan, Chandiran ; Paramanandam, Karthikeyan ; Srinivasan, Balamurugan</creator><creatorcontrib>Malak, Malak Fouad ; Narayanan, Sridharan Reghupathy ; Jayamurugan, Chandiran ; Paramanandam, Karthikeyan ; Srinivasan, Balamurugan</creatorcontrib><description>An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.</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=20210302&DB=EPODOC&CC=US&NR=10934856B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20210302&DB=EPODOC&CC=US&NR=10934856B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Malak, Malak Fouad</creatorcontrib><creatorcontrib>Narayanan, Sridharan Reghupathy</creatorcontrib><creatorcontrib>Jayamurugan, Chandiran</creatorcontrib><creatorcontrib>Paramanandam, Karthikeyan</creatorcontrib><creatorcontrib>Srinivasan, Balamurugan</creatorcontrib><title>Gas turbine engines with improved leading edge airfoil cooling</title><description>An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.</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>eNrjZLBzTyxWKCktSsrMS1VIzUsHUsUK5ZklGQqZuQVF-WWpKQo5qYkpmXnpCqkp6akKiZlFafmZOQrJ-fk5QEEeBta0xJziVF4ozc2g6OYa4uyhm1qQH59aXJCYnJqXWhIfGmxoYGlsYmFq5mRkTIwaAFcjMLo</recordid><startdate>20210302</startdate><enddate>20210302</enddate><creator>Malak, Malak Fouad</creator><creator>Narayanan, Sridharan Reghupathy</creator><creator>Jayamurugan, Chandiran</creator><creator>Paramanandam, Karthikeyan</creator><creator>Srinivasan, Balamurugan</creator><scope>EVB</scope></search><sort><creationdate>20210302</creationdate><title>Gas turbine engines with improved leading edge airfoil cooling</title><author>Malak, Malak Fouad ; Narayanan, Sridharan Reghupathy ; Jayamurugan, Chandiran ; Paramanandam, Karthikeyan ; Srinivasan, Balamurugan</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US10934856B23</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>Malak, Malak Fouad</creatorcontrib><creatorcontrib>Narayanan, Sridharan Reghupathy</creatorcontrib><creatorcontrib>Jayamurugan, Chandiran</creatorcontrib><creatorcontrib>Paramanandam, Karthikeyan</creatorcontrib><creatorcontrib>Srinivasan, Balamurugan</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Malak, Malak Fouad</au><au>Narayanan, Sridharan Reghupathy</au><au>Jayamurugan, Chandiran</au><au>Paramanandam, Karthikeyan</au><au>Srinivasan, Balamurugan</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Gas turbine engines with improved leading edge airfoil cooling</title><date>2021-03-02</date><risdate>2021</risdate><abstract>An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US10934856B2 |
| 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 | Gas turbine engines with improved leading edge airfoil cooling |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-26T19%3A44%3A59IST&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=Malak,%20Malak%20Fouad&rft.date=2021-03-02&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS10934856B2%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 |