OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE
A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a t...
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| creator | AZAD, GM SALAM LEE, CHING-PANG LAURELLO, VINCENT P MARTIN, NICHOLAS F., JR SHIVANAND, MANJIT THAM, KOK-MUN |
| description | A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path. |
| format | Patent |
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The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path.</description><language>eng ; fre ; ger</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>2015</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=20151223&DB=EPODOC&CC=EP&NR=2956629A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20151223&DB=EPODOC&CC=EP&NR=2956629A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>AZAD, GM SALAM</creatorcontrib><creatorcontrib>LEE, CHING-PANG</creatorcontrib><creatorcontrib>LAURELLO, VINCENT P</creatorcontrib><creatorcontrib>MARTIN, NICHOLAS F., JR</creatorcontrib><creatorcontrib>SHIVANAND, MANJIT</creatorcontrib><creatorcontrib>THAM, KOK-MUN</creatorcontrib><title>OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE</title><description>A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path.</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>2015</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZND2Dw1xDVII8vRVCHZ19FFwDA529XXyiVTw9FNwVAgJDXLy9HNVcPVzB1I8DKxpiTnFqbxQmptBwc01xNlDN7UgPz61uCAxOTUvtSTeNcDI0tTMzMjS0dCYCCUAD_0kSw</recordid><startdate>20151223</startdate><enddate>20151223</enddate><creator>AZAD, GM SALAM</creator><creator>LEE, CHING-PANG</creator><creator>LAURELLO, VINCENT P</creator><creator>MARTIN, NICHOLAS F., JR</creator><creator>SHIVANAND, MANJIT</creator><creator>THAM, KOK-MUN</creator><scope>EVB</scope></search><sort><creationdate>20151223</creationdate><title>OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE</title><author>AZAD, GM SALAM ; LEE, CHING-PANG ; LAURELLO, VINCENT P ; MARTIN, NICHOLAS F., JR ; SHIVANAND, MANJIT ; THAM, KOK-MUN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP2956629A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2015</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>AZAD, GM SALAM</creatorcontrib><creatorcontrib>LEE, CHING-PANG</creatorcontrib><creatorcontrib>LAURELLO, VINCENT P</creatorcontrib><creatorcontrib>MARTIN, NICHOLAS F., JR</creatorcontrib><creatorcontrib>SHIVANAND, MANJIT</creatorcontrib><creatorcontrib>THAM, KOK-MUN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>AZAD, GM SALAM</au><au>LEE, CHING-PANG</au><au>LAURELLO, VINCENT P</au><au>MARTIN, NICHOLAS F., JR</au><au>SHIVANAND, MANJIT</au><au>THAM, KOK-MUN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE</title><date>2015-12-23</date><risdate>2015</risdate><abstract>A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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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 | OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE |
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