PROCESS FOR REPLACING AN ABRADABLE ON THE FAN CASE OF A TURBOJET
L'invention propose un procédé simple et économique pour remplacer un abradable sur le carter de soufflante d'un turboréacteur. Ce procédé est remarquable en ce qu'on met en place contre l'abradable (80) une ceinture chauffante interne (100) et des secteurs de maintien (110) comp...
Gespeichert in:
| Hauptverfasser: | , , , |
|---|---|
| Format: | Patent |
| Sprache: | eng ; fre |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | HAMEL, YANNICK PONSEN, FRANCOIS VERRIERES, ALAIN LE SAINT, JACQUES |
| description | L'invention propose un procédé simple et économique pour remplacer un abradable sur le carter de soufflante d'un turboréacteur. Ce procédé est remarquable en ce qu'on met en place contre l'abradable (80) une ceinture chauffante interne (100) et des secteurs de maintien (110) comportant chacun une vessie (120) gonflable, l'abradable (80) et la couverture chauffante interne (100) étant intégralement pris en sandwich entre le carter de soufflante (60) et les vessies (120), les secteurs de maintien (110) étant eux-mêmes maintenus en place par une pluralité de brides (125) attachées au carter de soufflante (60) par les points de fixation (96).
The procedure is designed for use on a turbojet engine with a rotary section that has a fan stage with a hub and series of blades at the forward end of its shaft inside an annular casing (60) with an abradable layer (80) stuck to its inner surface (70). It consists of removing the worn abradable layer, cleaning and applying adhesive (82) to the casing's inner surface, and fitting the new abradable layer against it. The inner, sealing surface (84) of the abradable layer is then fitted with a heating band (100), to which a pressure is applied by at least three supporting sectors (110) with inflatable chambers (120), the sectors being held in place by brackets (125) attached to the fan casing by fixings (96). |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_CA2463180A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>CA2463180A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_CA2463180A13</originalsourceid><addsrcrecordid>eNrjZHAICPJ3dg0OVnDzD1IIcg3wcXT29HNXcPRTcHQKcnRxdPJxVfD3UwjxcFVwAwo6OwYD-W4KjgohoUFO_l6uITwMrGmJOcWpvFCam0HBzTXE2UM3tSA_PrW4IDE5NS-1JN7Z0cjEzNjQwsDR0JgIJQD7KSlJ</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>PROCESS FOR REPLACING AN ABRADABLE ON THE FAN CASE OF A TURBOJET</title><source>esp@cenet</source><creator>HAMEL, YANNICK ; PONSEN, FRANCOIS ; VERRIERES, ALAIN ; LE SAINT, JACQUES</creator><creatorcontrib>HAMEL, YANNICK ; PONSEN, FRANCOIS ; VERRIERES, ALAIN ; LE SAINT, JACQUES</creatorcontrib><description>L'invention propose un procédé simple et économique pour remplacer un abradable sur le carter de soufflante d'un turboréacteur. Ce procédé est remarquable en ce qu'on met en place contre l'abradable (80) une ceinture chauffante interne (100) et des secteurs de maintien (110) comportant chacun une vessie (120) gonflable, l'abradable (80) et la couverture chauffante interne (100) étant intégralement pris en sandwich entre le carter de soufflante (60) et les vessies (120), les secteurs de maintien (110) étant eux-mêmes maintenus en place par une pluralité de brides (125) attachées au carter de soufflante (60) par les points de fixation (96).
The procedure is designed for use on a turbojet engine with a rotary section that has a fan stage with a hub and series of blades at the forward end of its shaft inside an annular casing (60) with an abradable layer (80) stuck to its inner surface (70). It consists of removing the worn abradable layer, cleaning and applying adhesive (82) to the casing's inner surface, and fitting the new abradable layer against it. The inner, sealing surface (84) of the abradable layer is then fitted with a heating band (100), to which a pressure is applied by at least three supporting sectors (110) with inflatable chambers (120), the sectors being held in place by brackets (125) attached to the fan casing by fixings (96).</description><edition>7</edition><language>eng ; fre</language><subject>AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING ; BLASTING ; COMBINED OPERATIONS ; COMBUSTION ENGINES ; ENGINE PLANTS IN GENERAL ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MACHINE TOOLS ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; METAL-WORKING NOT OTHERWISE PROVIDED FOR ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; OTHER WORKING OF METAL ; PERFORMING OPERATIONS ; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR ; SHAPING OR JOINING OF PLASTICS ; STEAM ENGINES ; TRANSPORTING ; UNIVERSAL MACHINE TOOLS ; WEAPONS ; WORKING OF PLASTICS ; WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL</subject><creationdate>2004</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=20041022&DB=EPODOC&CC=CA&NR=2463180A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20041022&DB=EPODOC&CC=CA&NR=2463180A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>HAMEL, YANNICK</creatorcontrib><creatorcontrib>PONSEN, FRANCOIS</creatorcontrib><creatorcontrib>VERRIERES, ALAIN</creatorcontrib><creatorcontrib>LE SAINT, JACQUES</creatorcontrib><title>PROCESS FOR REPLACING AN ABRADABLE ON THE FAN CASE OF A TURBOJET</title><description>L'invention propose un procédé simple et économique pour remplacer un abradable sur le carter de soufflante d'un turboréacteur. Ce procédé est remarquable en ce qu'on met en place contre l'abradable (80) une ceinture chauffante interne (100) et des secteurs de maintien (110) comportant chacun une vessie (120) gonflable, l'abradable (80) et la couverture chauffante interne (100) étant intégralement pris en sandwich entre le carter de soufflante (60) et les vessies (120), les secteurs de maintien (110) étant eux-mêmes maintenus en place par une pluralité de brides (125) attachées au carter de soufflante (60) par les points de fixation (96).
The procedure is designed for use on a turbojet engine with a rotary section that has a fan stage with a hub and series of blades at the forward end of its shaft inside an annular casing (60) with an abradable layer (80) stuck to its inner surface (70). It consists of removing the worn abradable layer, cleaning and applying adhesive (82) to the casing's inner surface, and fitting the new abradable layer against it. The inner, sealing surface (84) of the abradable layer is then fitted with a heating band (100), to which a pressure is applied by at least three supporting sectors (110) with inflatable chambers (120), the sectors being held in place by brackets (125) attached to the fan casing by fixings (96).</description><subject>AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING</subject><subject>BLASTING</subject><subject>COMBINED OPERATIONS</subject><subject>COMBUSTION ENGINES</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MACHINE TOOLS</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>METAL-WORKING NOT OTHERWISE PROVIDED FOR</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>OTHER WORKING OF METAL</subject><subject>PERFORMING OPERATIONS</subject><subject>SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR</subject><subject>SHAPING OR JOINING OF PLASTICS</subject><subject>STEAM ENGINES</subject><subject>TRANSPORTING</subject><subject>UNIVERSAL MACHINE TOOLS</subject><subject>WEAPONS</subject><subject>WORKING OF PLASTICS</subject><subject>WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2004</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZHAICPJ3dg0OVnDzD1IIcg3wcXT29HNXcPRTcHQKcnRxdPJxVfD3UwjxcFVwAwo6OwYD-W4KjgohoUFO_l6uITwMrGmJOcWpvFCam0HBzTXE2UM3tSA_PrW4IDE5NS-1JN7Z0cjEzNjQwsDR0JgIJQD7KSlJ</recordid><startdate>20041022</startdate><enddate>20041022</enddate><creator>HAMEL, YANNICK</creator><creator>PONSEN, FRANCOIS</creator><creator>VERRIERES, ALAIN</creator><creator>LE SAINT, JACQUES</creator><scope>EVB</scope></search><sort><creationdate>20041022</creationdate><title>PROCESS FOR REPLACING AN ABRADABLE ON THE FAN CASE OF A TURBOJET</title><author>HAMEL, YANNICK ; PONSEN, FRANCOIS ; VERRIERES, ALAIN ; LE SAINT, JACQUES</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA2463180A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2004</creationdate><topic>AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING</topic><topic>BLASTING</topic><topic>COMBINED OPERATIONS</topic><topic>COMBUSTION ENGINES</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MACHINE TOOLS</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>METAL-WORKING NOT OTHERWISE PROVIDED FOR</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>OTHER WORKING OF METAL</topic><topic>PERFORMING OPERATIONS</topic><topic>SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR</topic><topic>SHAPING OR JOINING OF PLASTICS</topic><topic>STEAM ENGINES</topic><topic>TRANSPORTING</topic><topic>UNIVERSAL MACHINE TOOLS</topic><topic>WEAPONS</topic><topic>WORKING OF PLASTICS</topic><topic>WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL</topic><toplevel>online_resources</toplevel><creatorcontrib>HAMEL, YANNICK</creatorcontrib><creatorcontrib>PONSEN, FRANCOIS</creatorcontrib><creatorcontrib>VERRIERES, ALAIN</creatorcontrib><creatorcontrib>LE SAINT, JACQUES</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>HAMEL, YANNICK</au><au>PONSEN, FRANCOIS</au><au>VERRIERES, ALAIN</au><au>LE SAINT, JACQUES</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>PROCESS FOR REPLACING AN ABRADABLE ON THE FAN CASE OF A TURBOJET</title><date>2004-10-22</date><risdate>2004</risdate><abstract>L'invention propose un procédé simple et économique pour remplacer un abradable sur le carter de soufflante d'un turboréacteur. Ce procédé est remarquable en ce qu'on met en place contre l'abradable (80) une ceinture chauffante interne (100) et des secteurs de maintien (110) comportant chacun une vessie (120) gonflable, l'abradable (80) et la couverture chauffante interne (100) étant intégralement pris en sandwich entre le carter de soufflante (60) et les vessies (120), les secteurs de maintien (110) étant eux-mêmes maintenus en place par une pluralité de brides (125) attachées au carter de soufflante (60) par les points de fixation (96).
The procedure is designed for use on a turbojet engine with a rotary section that has a fan stage with a hub and series of blades at the forward end of its shaft inside an annular casing (60) with an abradable layer (80) stuck to its inner surface (70). It consists of removing the worn abradable layer, cleaning and applying adhesive (82) to the casing's inner surface, and fitting the new abradable layer against it. The inner, sealing surface (84) of the abradable layer is then fitted with a heating band (100), to which a pressure is applied by at least three supporting sectors (110) with inflatable chambers (120), the sectors being held in place by brackets (125) attached to the fan casing by fixings (96).</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng ; fre |
| recordid | cdi_epo_espacenet_CA2463180A1 |
| source | esp@cenet |
| subjects | AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING BLASTING COMBINED OPERATIONS COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL |
| title | PROCESS FOR REPLACING AN ABRADABLE ON THE FAN CASE OF A TURBOJET |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-24T12%3A23%3A21IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=HAMEL,%20YANNICK&rft.date=2004-10-22&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3ECA2463180A1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |