ROCKET NOZZLE THROAT INSERT
A rocket throat insert (112) including an annular body (120) having a radially inner annular wall portion (122) and a radially outer annular portion (124). The inner wall portion has a contoured radially inner surface (128) defining a nozzle throat (130). The outer portion includes an annular buttre...
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| creator | FOWLER, Gray BRENNAN, Michael |
| description | A rocket throat insert (112) including an annular body (120) having a radially inner annular wall portion (122) and a radially outer annular portion (124). The inner wall portion has a contoured radially inner surface (128) defining a nozzle throat (130). The outer portion includes an annular buttressing structure (132) supporting the inner wall portion and defining one or more insulation gaps (134) arranged annularly around the inner wall portion. The insulation gaps restrict the radial flow of heat through the annular body.
L'invention concerne un insert de col de fusée (112) comprenant un corps annulaire (120) ayant une portion de paroi annulaire radialement interne (122) et une portion annulaire radialement externe (124). La portion de paroi interne présente une surface radialement interne profilée (128) qui définit un col de tuyère (130). La portion externe comprend une structure de renfort annulaire (132) supportant la portion de paroi interne et définissant un ou plusieurs espaces d'isolation (134) disposés de façon annulaire autour de la portion de paroi interne. Les espaces d'isolation limitent le flux radial de chaleur à travers le corps annulaire. |
| format | Patent |
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L'invention concerne un insert de col de fusée (112) comprenant un corps annulaire (120) ayant une portion de paroi annulaire radialement interne (122) et une portion annulaire radialement externe (124). La portion de paroi interne présente une surface radialement interne profilée (128) qui définit un col de tuyère (130). La portion externe comprend une structure de renfort annulaire (132) supportant la portion de paroi interne et définissant un ou plusieurs espaces d'isolation (134) disposés de façon annulaire autour de la portion de paroi interne. Les espaces d'isolation limitent le flux radial de chaleur à travers le corps annulaire.</description><language>eng ; fre</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; 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=20190620&DB=EPODOC&CC=WO&NR=2019118259A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20190620&DB=EPODOC&CC=WO&NR=2019118259A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>FOWLER, Gray</creatorcontrib><creatorcontrib>BRENNAN, Michael</creatorcontrib><title>ROCKET NOZZLE THROAT INSERT</title><description>A rocket throat insert (112) including an annular body (120) having a radially inner annular wall portion (122) and a radially outer annular portion (124). The inner wall portion has a contoured radially inner surface (128) defining a nozzle throat (130). The outer portion includes an annular buttressing structure (132) supporting the inner wall portion and defining one or more insulation gaps (134) arranged annularly around the inner wall portion. The insulation gaps restrict the radial flow of heat through the annular body.
L'invention concerne un insert de col de fusée (112) comprenant un corps annulaire (120) ayant une portion de paroi annulaire radialement interne (122) et une portion annulaire radialement externe (124). La portion de paroi interne présente une surface radialement interne profilée (128) qui définit un col de tuyère (130). La portion externe comprend une structure de renfort annulaire (132) supportant la portion de paroi interne et définissant un ou plusieurs espaces d'isolation (134) disposés de façon annulaire autour de la portion de paroi interne. Les espaces d'isolation limitent le flux radial de chaleur à travers le corps annulaire.</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</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>eNrjZJAO8nf2dg1R8POPivJxVQjxCPJ3DFHw9At2DQrhYWBNS8wpTuWF0twMym6uIc4euqkF-fGpxQWJyal5qSXx4f5GBoaWhoYWRqaWjobGxKkCAOk3Ia8</recordid><startdate>20190620</startdate><enddate>20190620</enddate><creator>FOWLER, Gray</creator><creator>BRENNAN, Michael</creator><scope>EVB</scope></search><sort><creationdate>20190620</creationdate><title>ROCKET NOZZLE THROAT INSERT</title><author>FOWLER, Gray ; BRENNAN, Michael</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_WO2019118259A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2019</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>FOWLER, Gray</creatorcontrib><creatorcontrib>BRENNAN, Michael</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>FOWLER, Gray</au><au>BRENNAN, Michael</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>ROCKET NOZZLE THROAT INSERT</title><date>2019-06-20</date><risdate>2019</risdate><abstract>A rocket throat insert (112) including an annular body (120) having a radially inner annular wall portion (122) and a radially outer annular portion (124). The inner wall portion has a contoured radially inner surface (128) defining a nozzle throat (130). The outer portion includes an annular buttressing structure (132) supporting the inner wall portion and defining one or more insulation gaps (134) arranged annularly around the inner wall portion. The insulation gaps restrict the radial flow of heat through the annular body.
L'invention concerne un insert de col de fusée (112) comprenant un corps annulaire (120) ayant une portion de paroi annulaire radialement interne (122) et une portion annulaire radialement externe (124). La portion de paroi interne présente une surface radialement interne profilée (128) qui définit un col de tuyère (130). La portion externe comprend une structure de renfort annulaire (132) supportant la portion de paroi interne et définissant un ou plusieurs espaces d'isolation (134) disposés de façon annulaire autour de la portion de paroi interne. Les espaces d'isolation limitent le flux radial de chaleur à travers le corps annulaire.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre |
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| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | ROCKET NOZZLE THROAT INSERT |
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