Deflection mitigation structure for combustion system
A combustion section for a gas turbine engine includes an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material...
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| creator | VENZON ANTHONY JOSEPH PAYNE JEREMY KEVIN PATEL NARENDRA KUMAR |
| description | A combustion section for a gas turbine engine includes an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material definesa second heat transfer coefficient less than the first heat transfer coefficient.
一种用于燃气涡轮发动机的燃烧区段包括内壳体，该内壳体包括限定压力容器的内径和第一传热系数的第一材料。第二材料至少部分地在第一材料的外径上延伸。第二材料径向设置在第一材料和燃烧器衬里之间。第二材料限定小于第一传热系数的第二传热系数。 |
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一种用于燃气涡轮发动机的燃烧区段包括内壳体，该内壳体包括限定压力容器的内径和第一传热系数的第一材料。第二材料至少部分地在第一材料的外径上延伸。第二材料径向设置在第一材料和燃烧器衬里之间。第二材料限定小于第一传热系数的第二传热系数。</description><language>chi ; eng</language><subject>BLASTING ; COMBUSTION APPARATUS ; COMBUSTION PROCESSES ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2019</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=20191220&DB=EPODOC&CC=CN&NR=110594785A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20191220&DB=EPODOC&CC=CN&NR=110594785A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>VENZON ANTHONY JOSEPH</creatorcontrib><creatorcontrib>PAYNE JEREMY KEVIN</creatorcontrib><creatorcontrib>PATEL NARENDRA KUMAR</creatorcontrib><title>Deflection mitigation structure for combustion system</title><description>A combustion section for a gas turbine engine includes an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material definesa second heat transfer coefficient less than the first heat transfer coefficient.
一种用于燃气涡轮发动机的燃烧区段包括内壳体，该内壳体包括限定压力容器的内径和第一传热系数的第一材料。第二材料至少部分地在第一材料的外径上延伸。第二材料径向设置在第一材料和燃烧器衬里之间。第二材料限定小于第一传热系数的第二传热系数。</description><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION PROCESSES</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDB1SU3LSU0uyczPU8jNLMlMTwQzi0uKSpNLSotSFdLyixSS83OTSoshEpXFJam5PAysaYk5xam8UJqbQdHNNcTZQze1ID8-tbggMTk1L7Uk3tnP0NDA1NLE3MLU0ZgYNQDLJS4e</recordid><startdate>20191220</startdate><enddate>20191220</enddate><creator>VENZON ANTHONY JOSEPH</creator><creator>PAYNE JEREMY KEVIN</creator><creator>PATEL NARENDRA KUMAR</creator><scope>EVB</scope></search><sort><creationdate>20191220</creationdate><title>Deflection mitigation structure for combustion system</title><author>VENZON ANTHONY JOSEPH ; PAYNE JEREMY KEVIN ; PATEL NARENDRA KUMAR</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN110594785A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2019</creationdate><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION PROCESSES</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>VENZON ANTHONY JOSEPH</creatorcontrib><creatorcontrib>PAYNE JEREMY KEVIN</creatorcontrib><creatorcontrib>PATEL NARENDRA KUMAR</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>VENZON ANTHONY JOSEPH</au><au>PAYNE JEREMY KEVIN</au><au>PATEL NARENDRA KUMAR</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Deflection mitigation structure for combustion system</title><date>2019-12-20</date><risdate>2019</risdate><abstract>A combustion section for a gas turbine engine includes an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material definesa second heat transfer coefficient less than the first heat transfer coefficient.
一种用于燃气涡轮发动机的燃烧区段包括内壳体，该内壳体包括限定压力容器的内径和第一传热系数的第一材料。第二材料至少部分地在第一材料的外径上延伸。第二材料径向设置在第一材料和燃烧器衬里之间。第二材料限定小于第一传热系数的第二传热系数。</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Deflection mitigation structure for combustion system |
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