AERONAUTICAL THRUSTER

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 a...

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Hauptverfasser:	LEBEAULT, Eva Julie, LALLIA, Mathieu Patrick Jean-Louis, GEA AGUILERA, Fernando, BINDER, Anthony
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS PARACHUTES PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TRANSPORTING WEAPONS
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creator	LEBEAULT, Eva Julie LALLIA, Mathieu Patrick Jean-Louis GEA AGUILERA, Fernando BINDER, Anthony
description	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). 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).
format	Patent
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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).</description><language>eng ; fre</language><subject>AEROPLANES ; AIR INTAKES FOR JET-PROPULSION PLANTS ; AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; COSMONAUTICS ; ENGINE PLANTS IN GENERAL ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GAS-TURBINE PLANTS ; HEATING ; HELICOPTERS ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; NON-POSITIVE DISPLACEMENT PUMPS ; PARACHUTES ; PERFORMING OPERATIONS ; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS ; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS ; 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=20230914&DB=EPODOC&CC=WO&NR=2023170358A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20230914&DB=EPODOC&CC=WO&NR=2023170358A1$$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>AERONAUTICAL THRUSTER</title><description>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). 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).</description><subject>AEROPLANES</subject><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>COSMONAUTICS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</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>NON-POSITIVE DISPLACEMENT PUMPS</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</subject><subject>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</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>eNrjZBB1dA3y93MMDfF0dvRRCPEICg0OcQ3iYWBNS8wpTuWF0twMym6uIc4euqkF-fGpxQWJyal5qSXx4f5GBkbGhuYGxqYWjobGxKkCAChgIAM</recordid><startdate>20230914</startdate><enddate>20230914</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>20230914</creationdate><title>AERONAUTICAL THRUSTER</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_WO2023170358A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2023</creationdate><topic>AEROPLANES</topic><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>COSMONAUTICS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</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>NON-POSITIVE DISPLACEMENT PUMPS</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS</topic><topic>PUMPS FOR LIQUIDS OR ELASTIC FLUIDS</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>AERONAUTICAL THRUSTER</title><date>2023-09-14</date><risdate>2023</risdate><abstract>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). 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).</abstract><oa>free_for_read</oa></addata></record>
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language	eng ; fre
recordid	cdi_epo_espacenet_WO2023170358A1
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subjects	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS PARACHUTES PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TRANSPORTING WEAPONS
title	AERONAUTICAL THRUSTER
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