CERAMIC CENTERBODY FOR AN AIRCRAFT GAS TURBINE ENGINE AND METHOD OF MAKING
A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed in...
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| creator | RENGGLI, BERNARD JAMES MILLER, JEFFREY FRANKLIN |
| description | A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed into a conical shape having a fore end (128) and an aft end (126). The centerbody includes a means for mechanical attachment (130) circumferentially oriented around the fore end of the centerbody. The fore end further includes additional plies oriented in a third preselected direction, thereby providing additional strength to for mechanical attachment.
La présente invention concerne un anneau central en céramique (120) d'un moteur à turbine à gaz d'aéronef. Selon l'invention, l'anneau central en céramique (120) comprend une structure de fibres entrelacées comportant des fibres orientées dans des directions sensiblement transversales et une matrice de céramique entourant la structure de fibres de céramique. Les fibres et la matrice de céramique sont réalisées avec une forme conique ayant une extrémité avant (128) et une extrémité arrière (126). L'anneau central comprend un moyen de fixation mécanique (130) orienté de manière circonférentielle autour de l'extrémité avant de l'anneau central. L'extrémité avant comprend en outre des épaisseurs supplémentaires orientées dans une troisième direction choisie au préalable, ce qui fournit une résistance supplémentaire pour la fixation mécanique. |
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La présente invention concerne un anneau central en céramique (120) d'un moteur à turbine à gaz d'aéronef. Selon l'invention, l'anneau central en céramique (120) comprend une structure de fibres entrelacées comportant des fibres orientées dans des directions sensiblement transversales et une matrice de céramique entourant la structure de fibres de céramique. Les fibres et la matrice de céramique sont réalisées avec une forme conique ayant une extrémité avant (128) et une extrémité arrière (126). L'anneau central comprend un moyen de fixation mécanique (130) orienté de manière circonférentielle autour de l'extrémité avant de l'anneau central. L'extrémité avant comprend en outre des épaisseurs supplémentaires orientées dans une troisième direction choisie au préalable, ce qui fournit une résistance supplémentaire pour la fixation mécanique.</description><language>eng ; fre</language><subject>ARTIFICIAL STONE ; BLASTING ; CEMENTS ; CERAMICS ; CHEMISTRY ; COMBUSTION ENGINES ; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDINGMATERIALS ; CONCRETE ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LAYERED PRODUCTS ; LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM ; LIGHTING ; LIME, MAGNESIA ; MECHANICAL ENGINEERING ; METALLURGY ; PERFORMING OPERATIONS ; REFRACTORIES ; SLAG ; TRANSPORTING ; TREATMENT OF NATURAL STONE ; WEAPONS</subject><creationdate>2014</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=20140417&DB=EPODOC&CC=CA&NR=2879336A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76294</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20140417&DB=EPODOC&CC=CA&NR=2879336A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>RENGGLI, BERNARD JAMES</creatorcontrib><creatorcontrib>MILLER, JEFFREY FRANKLIN</creatorcontrib><title>CERAMIC CENTERBODY FOR AN AIRCRAFT GAS TURBINE ENGINE AND METHOD OF MAKING</title><description>A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed into a conical shape having a fore end (128) and an aft end (126). The centerbody includes a means for mechanical attachment (130) circumferentially oriented around the fore end of the centerbody. The fore end further includes additional plies oriented in a third preselected direction, thereby providing additional strength to for mechanical attachment.
La présente invention concerne un anneau central en céramique (120) d'un moteur à turbine à gaz d'aéronef. Selon l'invention, l'anneau central en céramique (120) comprend une structure de fibres entrelacées comportant des fibres orientées dans des directions sensiblement transversales et une matrice de céramique entourant la structure de fibres de céramique. Les fibres et la matrice de céramique sont réalisées avec une forme conique ayant une extrémité avant (128) et une extrémité arrière (126). L'anneau central comprend un moyen de fixation mécanique (130) orienté de manière circonférentielle autour de l'extrémité avant de l'anneau central. L'extrémité avant comprend en outre des épaisseurs supplémentaires orientées dans une troisième direction choisie au préalable, ce qui fournit une résistance supplémentaire pour la fixation mécanique.</description><subject>ARTIFICIAL STONE</subject><subject>BLASTING</subject><subject>CEMENTS</subject><subject>CERAMICS</subject><subject>CHEMISTRY</subject><subject>COMBUSTION ENGINES</subject><subject>COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDINGMATERIALS</subject><subject>CONCRETE</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LAYERED PRODUCTS</subject><subject>LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM</subject><subject>LIGHTING</subject><subject>LIME, MAGNESIA</subject><subject>MECHANICAL ENGINEERING</subject><subject>METALLURGY</subject><subject>PERFORMING OPERATIONS</subject><subject>REFRACTORIES</subject><subject>SLAG</subject><subject>TRANSPORTING</subject><subject>TREATMENT OF NATURAL STONE</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2014</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyjsKAjEQANA0FqLeYS5goQE_5exkko2SCYzZwmpZJFaiC-v9EcEDWL3mzc2JWDFFAmIprE12V_BZAQUwKin6AgEvUDptojCwhC8oDhKXNjvIHhKeo4Slmd2Hx1RXPxcGPBdq13V89XUah1t91ndPuD3sj9bucGP_KB-87SxS</recordid><startdate>20140417</startdate><enddate>20140417</enddate><creator>RENGGLI, BERNARD JAMES</creator><creator>MILLER, JEFFREY FRANKLIN</creator><scope>EVB</scope></search><sort><creationdate>20140417</creationdate><title>CERAMIC CENTERBODY FOR AN AIRCRAFT GAS TURBINE ENGINE AND METHOD OF MAKING</title><author>RENGGLI, BERNARD JAMES ; MILLER, JEFFREY FRANKLIN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA2879336A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2014</creationdate><topic>ARTIFICIAL STONE</topic><topic>BLASTING</topic><topic>CEMENTS</topic><topic>CERAMICS</topic><topic>CHEMISTRY</topic><topic>COMBUSTION ENGINES</topic><topic>COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDINGMATERIALS</topic><topic>CONCRETE</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LAYERED PRODUCTS</topic><topic>LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM</topic><topic>LIGHTING</topic><topic>LIME, MAGNESIA</topic><topic>MECHANICAL ENGINEERING</topic><topic>METALLURGY</topic><topic>PERFORMING OPERATIONS</topic><topic>REFRACTORIES</topic><topic>SLAG</topic><topic>TRANSPORTING</topic><topic>TREATMENT OF NATURAL STONE</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>RENGGLI, BERNARD JAMES</creatorcontrib><creatorcontrib>MILLER, JEFFREY FRANKLIN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>RENGGLI, BERNARD JAMES</au><au>MILLER, JEFFREY FRANKLIN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>CERAMIC CENTERBODY FOR AN AIRCRAFT GAS TURBINE ENGINE AND METHOD OF MAKING</title><date>2014-04-17</date><risdate>2014</risdate><abstract>A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed into a conical shape having a fore end (128) and an aft end (126). The centerbody includes a means for mechanical attachment (130) circumferentially oriented around the fore end of the centerbody. The fore end further includes additional plies oriented in a third preselected direction, thereby providing additional strength to for mechanical attachment.
La présente invention concerne un anneau central en céramique (120) d'un moteur à turbine à gaz d'aéronef. Selon l'invention, l'anneau central en céramique (120) comprend une structure de fibres entrelacées comportant des fibres orientées dans des directions sensiblement transversales et une matrice de céramique entourant la structure de fibres de céramique. Les fibres et la matrice de céramique sont réalisées avec une forme conique ayant une extrémité avant (128) et une extrémité arrière (126). L'anneau central comprend un moyen de fixation mécanique (130) orienté de manière circonférentielle autour de l'extrémité avant de l'anneau central. L'extrémité avant comprend en outre des épaisseurs supplémentaires orientées dans une troisième direction choisie au préalable, ce qui fournit une résistance supplémentaire pour la fixation mécanique.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | ARTIFICIAL STONE BLASTING CEMENTS CERAMICS CHEMISTRY COMBUSTION ENGINES COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDINGMATERIALS CONCRETE HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LAYERED PRODUCTS LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM LIGHTING LIME, MAGNESIA MECHANICAL ENGINEERING METALLURGY PERFORMING OPERATIONS REFRACTORIES SLAG TRANSPORTING TREATMENT OF NATURAL STONE WEAPONS |
| title | CERAMIC CENTERBODY FOR AN AIRCRAFT GAS TURBINE ENGINE AND METHOD OF MAKING |
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