PROPULSEUR AERONAUTIQUE
Propulseur aéronautique (10) d'axe longitudinal (X) comprenant un moyeu (12), une rangée annulaire de pales rotoriques amont (14) non carénées et une rangée annulaire de pales statoriques aval (16) non carénées, chaque pale statorique aval (16) étant à calage variable, et dans lequel au moins l...
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| creator | LEBEAULT, Eva Julie LALLIA, Mathieu Patrick Jean-Louis GEA AGUILERA, Fernando BINDER, Anthony |
| description | Propulseur aéronautique (10) d'axe longitudinal (X) comprenant un moyeu (12), une rangée annulaire de pales rotoriques amont (14) non carénées et une rangée annulaire de pales statoriques aval (16) non carénées, chaque pale statorique aval (16) étant à calage variable, et dans lequel au moins l'une des pales statoriques aval (16) est dans une configuration à calage fermé relativement à une autre des pales statoriques aval (16) en ce qu'elle présente un angle de calage (γ) inférieur à l'angle de calage (γ) de l'autre pale statorique aval (16). Figure de l'abrégé : Figure 2
The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each downstream stator blade (16) being of variable pitch, and wherein at least one of the downstream stator blades (16) is in a fixed-pitch configuration relative to another of the downstream stator blades (16) in that it has a pitch angle (γ) less than the pitch angle (γ) of the other downstream stator blade (16). |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_FR3133367A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>FR3133367A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_FR3133367A13</originalsourceid><addsrcrecordid>eNrjZBAPCPIPCPUJdg0NUnB0DfL3cwwN8QwMdeVhYE1LzClO5YXS3AwKbq4hzh66qQX58anFBYnJqXmpJfFuQcaGxsbGZuaOhsZEKAEAwcYfdA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>PROPULSEUR AERONAUTIQUE</title><source>esp@cenet</source><creator>LEBEAULT, Eva Julie ; LALLIA, Mathieu Patrick Jean-Louis ; GEA AGUILERA, Fernando ; BINDER, Anthony</creator><creatorcontrib>LEBEAULT, Eva Julie ; LALLIA, Mathieu Patrick Jean-Louis ; GEA AGUILERA, Fernando ; BINDER, Anthony</creatorcontrib><description>Propulseur aéronautique (10) d'axe longitudinal (X) comprenant un moyeu (12), une rangée annulaire de pales rotoriques amont (14) non carénées et une rangée annulaire de pales statoriques aval (16) non carénées, chaque pale statorique aval (16) étant à calage variable, et dans lequel au moins l'une des pales statoriques aval (16) est dans une configuration à calage fermé relativement à une autre des pales statoriques aval (16) en ce qu'elle présente un angle de calage (γ) inférieur à l'angle de calage (γ) de l'autre pale statorique aval (16). Figure de l'abrégé : Figure 2
The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each downstream stator blade (16) being of variable pitch, and wherein at least one of the downstream stator blades (16) is in a fixed-pitch configuration relative to another of the downstream stator blades (16) in that it has a pitch angle (γ) less than the pitch angle (γ) of the other downstream stator blade (16).</description><language>fre</language><subject>AEROPLANES ; AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; BLASTING ; COSMONAUTICS ; ENGINE PLANTS IN GENERAL ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; HEATING ; HELICOPTERS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; PARACHUTES ; PERFORMING OPERATIONS ; STEAM ENGINES ; TRANSPORTING ; WEAPONS</subject><creationdate>2023</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=20230915&DB=EPODOC&CC=FR&NR=3133367A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20230915&DB=EPODOC&CC=FR&NR=3133367A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>LEBEAULT, Eva Julie</creatorcontrib><creatorcontrib>LALLIA, Mathieu Patrick Jean-Louis</creatorcontrib><creatorcontrib>GEA AGUILERA, Fernando</creatorcontrib><creatorcontrib>BINDER, Anthony</creatorcontrib><title>PROPULSEUR AERONAUTIQUE</title><description>Propulseur aéronautique (10) d'axe longitudinal (X) comprenant un moyeu (12), une rangée annulaire de pales rotoriques amont (14) non carénées et une rangée annulaire de pales statoriques aval (16) non carénées, chaque pale statorique aval (16) étant à calage variable, et dans lequel au moins l'une des pales statoriques aval (16) est dans une configuration à calage fermé relativement à une autre des pales statoriques aval (16) en ce qu'elle présente un angle de calage (γ) inférieur à l'angle de calage (γ) de l'autre pale statorique aval (16). Figure de l'abrégé : Figure 2
The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each downstream stator blade (16) being of variable pitch, and wherein at least one of the downstream stator blades (16) is in a fixed-pitch configuration relative to another of the downstream stator blades (16) in that it has a pitch angle (γ) less than the pitch angle (γ) of the other downstream stator blade (16).</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COSMONAUTICS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>STEAM ENGINES</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBAPCPIPCPUJdg0NUnB0DfL3cwwN8QwMdeVhYE1LzClO5YXS3AwKbq4hzh66qQX58anFBYnJqXmpJfFuQcaGxsbGZuaOhsZEKAEAwcYfdA</recordid><startdate>20230915</startdate><enddate>20230915</enddate><creator>LEBEAULT, Eva Julie</creator><creator>LALLIA, Mathieu Patrick Jean-Louis</creator><creator>GEA AGUILERA, Fernando</creator><creator>BINDER, Anthony</creator><scope>EVB</scope></search><sort><creationdate>20230915</creationdate><title>PROPULSEUR AERONAUTIQUE</title><author>LEBEAULT, Eva Julie ; LALLIA, Mathieu Patrick Jean-Louis ; GEA AGUILERA, Fernando ; BINDER, Anthony</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_FR3133367A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>fre</language><creationdate>2023</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COSMONAUTICS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>STEAM ENGINES</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>LEBEAULT, Eva Julie</creatorcontrib><creatorcontrib>LALLIA, Mathieu Patrick Jean-Louis</creatorcontrib><creatorcontrib>GEA AGUILERA, Fernando</creatorcontrib><creatorcontrib>BINDER, Anthony</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>LEBEAULT, Eva Julie</au><au>LALLIA, Mathieu Patrick Jean-Louis</au><au>GEA AGUILERA, Fernando</au><au>BINDER, Anthony</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>PROPULSEUR AERONAUTIQUE</title><date>2023-09-15</date><risdate>2023</risdate><abstract>Propulseur aéronautique (10) d'axe longitudinal (X) comprenant un moyeu (12), une rangée annulaire de pales rotoriques amont (14) non carénées et une rangée annulaire de pales statoriques aval (16) non carénées, chaque pale statorique aval (16) étant à calage variable, et dans lequel au moins l'une des pales statoriques aval (16) est dans une configuration à calage fermé relativement à une autre des pales statoriques aval (16) en ce qu'elle présente un angle de calage (γ) inférieur à l'angle de calage (γ) de l'autre pale statorique aval (16). Figure de l'abrégé : Figure 2
The invention relates to an aeronautical thruster (10) with a longitudinal axis (X), comprising a hub (12), an annular row of non-ducted upstream rotor blades (14) and an annular row of non-ducted downstream stator blades (16), each downstream stator blade (16) being of variable pitch, and wherein at least one of the downstream stator blades (16) is in a fixed-pitch configuration relative to another of the downstream stator blades (16) in that it has a pitch angle (γ) less than the pitch angle (γ) of the other downstream stator blade (16).</abstract><oa>free_for_read</oa></addata></record> |
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| language | fre |
| recordid | cdi_epo_espacenet_FR3133367A1 |
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| subjects | AEROPLANES AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HELICOPTERS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS |
| title | PROPULSEUR AERONAUTIQUE |
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