COOLING VALVE FOR ROCKET ENGINE WITH CRYOGENIC PROPELLANTS AND ROCKET ENGINE COMPRISING SUCH A COOLING VALVE
Vanne de mise en froid pour moteur-fusée (10), comprenant un carter (12) pourvu d'un passage (14) s'étendant selon une direction axiale (X) et un clapet (16) logé dans le carter (12) et mobile par rapport au carter (12) selon la direction axiale (X), le clapet (16) comprenant une tige (16B...
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| creator | FAYE, Olivier NOMERANGE, Philippe |
| description | Vanne de mise en froid pour moteur-fusée (10), comprenant un carter (12) pourvu d'un passage (14) s'étendant selon une direction axiale (X) et un clapet (16) logé dans le carter (12) et mobile par rapport au carter (12) selon la direction axiale (X), le clapet (16) comprenant une tige (16B) s'étendant selon la direction axiale (X) et une tête de fermeture/ouverture du passage (16B) solidaire de la tige (16B), la tige (16B) étant couplée au carter (12) par au moins un élément bilame (18, 18') configuré pour se déformer selon la direction axiale (X) en fonction de la température ambiante au sein du passage (14)
To provide a cooling valve for a rocket engine with an improved cryogenic propellant, a rocket engine with a cryogenic propellant comprising the valve, and a spacecraft comprising the rocket engine.SOLUTION: A cooling valve 10 for a rocket engine includes a casing 12 having a passage 14 extending along an axial direction X, and a valve 16 that is housed in the casing 12 and is movable with respect to the casing 12 along the axial direction X. In the cooling valve 10 for a rocket engine, the valve 16 comprises a stem 16B extending along the axial direction X, and a head portion that is connected to the stem 16B to closely close or open the passage 14. The stem 16B is coupled to the casing 12 by at least one binary metal element 18, 18' which is configured to deform along the axial direction X as a function of the ambient temperature in the passage 14.SELECTED DRAWING: Figure 2 |
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To provide a cooling valve for a rocket engine with an improved cryogenic propellant, a rocket engine with a cryogenic propellant comprising the valve, and a spacecraft comprising the rocket engine.SOLUTION: A cooling valve 10 for a rocket engine includes a casing 12 having a passage 14 extending along an axial direction X, and a valve 16 that is housed in the casing 12 and is movable with respect to the casing 12 along the axial direction X. In the cooling valve 10 for a rocket engine, the valve 16 comprises a stem 16B extending along the axial direction X, and a head portion that is connected to the stem 16B to closely close or open the passage 14. The stem 16B is coupled to the casing 12 by at least one binary metal element 18, 18' which is configured to deform along the axial direction X as a function of the ambient temperature in the passage 14.SELECTED DRAWING: Figure 2</description><language>eng ; fre ; ger</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; 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=20211124&DB=EPODOC&CC=EP&NR=3913209A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20211124&DB=EPODOC&CC=EP&NR=3913209A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>FAYE, Olivier</creatorcontrib><creatorcontrib>NOMERANGE, Philippe</creatorcontrib><title>COOLING VALVE FOR ROCKET ENGINE WITH CRYOGENIC PROPELLANTS AND ROCKET ENGINE COMPRISING SUCH A COOLING VALVE</title><description>Vanne de mise en froid pour moteur-fusée (10), comprenant un carter (12) pourvu d'un passage (14) s'étendant selon une direction axiale (X) et un clapet (16) logé dans le carter (12) et mobile par rapport au carter (12) selon la direction axiale (X), le clapet (16) comprenant une tige (16B) s'étendant selon la direction axiale (X) et une tête de fermeture/ouverture du passage (16B) solidaire de la tige (16B), la tige (16B) étant couplée au carter (12) par au moins un élément bilame (18, 18') configuré pour se déformer selon la direction axiale (X) en fonction de la température ambiante au sein du passage (14)
To provide a cooling valve for a rocket engine with an improved cryogenic propellant, a rocket engine with a cryogenic propellant comprising the valve, and a spacecraft comprising the rocket engine.SOLUTION: A cooling valve 10 for a rocket engine includes a casing 12 having a passage 14 extending along an axial direction X, and a valve 16 that is housed in the casing 12 and is movable with respect to the casing 12 along the axial direction X. In the cooling valve 10 for a rocket engine, the valve 16 comprises a stem 16B extending along the axial direction X, and a head portion that is connected to the stem 16B to closely close or open the passage 14. The stem 16B is coupled to the casing 12 by at least one binary metal element 18, 18' which is configured to deform along the axial direction X as a function of the ambient temperature in the passage 14.SELECTED DRAWING: Figure 2</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>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNzLEKwjAQgOEsDqK-w72AYM3UMZzXJBhzIYktTqVInIoW6vsjgotOTv_y8S_FiMzOeg2tci1BwxEi45EykNfWE3Q2G8B4YU3eIoTIgZxTPidQ_vCDkU8h2vT-pTMaUPC1X4vFbRjnsvl0JaChjGZbpkdf5mm4lnt59hRkXcn9rlaV_IO8AIeNNjs</recordid><startdate>20211124</startdate><enddate>20211124</enddate><creator>FAYE, Olivier</creator><creator>NOMERANGE, Philippe</creator><scope>EVB</scope></search><sort><creationdate>20211124</creationdate><title>COOLING VALVE FOR ROCKET ENGINE WITH CRYOGENIC PROPELLANTS AND ROCKET ENGINE COMPRISING SUCH A COOLING VALVE</title><author>FAYE, Olivier ; NOMERANGE, Philippe</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3913209A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2021</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>FAYE, Olivier</creatorcontrib><creatorcontrib>NOMERANGE, Philippe</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>FAYE, Olivier</au><au>NOMERANGE, Philippe</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>COOLING VALVE FOR ROCKET ENGINE WITH CRYOGENIC PROPELLANTS AND ROCKET ENGINE COMPRISING SUCH A COOLING VALVE</title><date>2021-11-24</date><risdate>2021</risdate><abstract>Vanne de mise en froid pour moteur-fusée (10), comprenant un carter (12) pourvu d'un passage (14) s'étendant selon une direction axiale (X) et un clapet (16) logé dans le carter (12) et mobile par rapport au carter (12) selon la direction axiale (X), le clapet (16) comprenant une tige (16B) s'étendant selon la direction axiale (X) et une tête de fermeture/ouverture du passage (16B) solidaire de la tige (16B), la tige (16B) étant couplée au carter (12) par au moins un élément bilame (18, 18') configuré pour se déformer selon la direction axiale (X) en fonction de la température ambiante au sein du passage (14)
To provide a cooling valve for a rocket engine with an improved cryogenic propellant, a rocket engine with a cryogenic propellant comprising the valve, and a spacecraft comprising the rocket engine.SOLUTION: A cooling valve 10 for a rocket engine includes a casing 12 having a passage 14 extending along an axial direction X, and a valve 16 that is housed in the casing 12 and is movable with respect to the casing 12 along the axial direction X. In the cooling valve 10 for a rocket engine, the valve 16 comprises a stem 16B extending along the axial direction X, and a head portion that is connected to the stem 16B to closely close or open the passage 14. The stem 16B is coupled to the casing 12 by at least one binary metal element 18, 18' which is configured to deform along the axial direction X as a function of the ambient temperature in the passage 14.SELECTED DRAWING: Figure 2</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | COOLING VALVE FOR ROCKET ENGINE WITH CRYOGENIC PROPELLANTS AND ROCKET ENGINE COMPRISING SUCH A COOLING VALVE |
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