AIRCRAFT TURBINE ENGINE
Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30)...
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| creator | SOULAT, Laurent SCHVALLINGER, Michaël Franck Antoine SECONDAT DE MONTESQUIEU, Antoine Claude Baudouin MARTINEZ LUQUE, Raul GUEGAN, Damien Bernard Emeric |
| description | Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30) and configured to divide the primary airflow (18) into two to form the secondary air flows (20, 22); - first variable guide vanes (40) which are distributed around the shaft and each comprise a leading edge (40a) which is located upstream of the separator (24) and trailing edges (40b, 40c) which are located in the secondary airflows (20, 22); - and fixed guide vanes (42) which are distributed around the shaft in the external airflow and downstream of the first variable vanes (40). |
| format | Patent |
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- a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30) and configured to divide the primary airflow (18) into two to form the secondary air flows (20, 22); - first variable guide vanes (40) which are distributed around the shaft and each comprise a leading edge (40a) which is located upstream of the separator (24) and trailing edges (40b, 40c) which are located in the secondary airflows (20, 22); - and fixed guide vanes (42) which are distributed around the shaft in the external airflow and downstream of the first variable vanes (40).</description><language>eng ; fre ; ger</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINE PLANTS IN GENERAL ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; 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- a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30) and configured to divide the primary airflow (18) into two to form the secondary air flows (20, 22); - first variable guide vanes (40) which are distributed around the shaft and each comprise a leading edge (40a) which is located upstream of the separator (24) and trailing edges (40b, 40c) which are located in the secondary airflows (20, 22); - and fixed guide vanes (42) which are distributed around the shaft in the external airflow and downstream of the first variable vanes (40).</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION 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>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZBB39AxyDnJ0C1EICQ1y8vRzVXD1cwdSPAysaYk5xam8UJqbQcHNNcTZQze1ID8-tbggMTk1L7Uk3jXAxMTEwtLY2NHQmAglAJSnHwc</recordid><startdate>20241023</startdate><enddate>20241023</enddate><creator>SOULAT, Laurent</creator><creator>SCHVALLINGER, Michaël Franck Antoine</creator><creator>SECONDAT DE MONTESQUIEU, Antoine Claude Baudouin</creator><creator>MARTINEZ LUQUE, Raul</creator><creator>GUEGAN, Damien Bernard Emeric</creator><scope>EVB</scope></search><sort><creationdate>20241023</creationdate><title>AIRCRAFT TURBINE ENGINE</title><author>SOULAT, Laurent ; SCHVALLINGER, Michaël Franck Antoine ; SECONDAT DE MONTESQUIEU, Antoine Claude Baudouin ; MARTINEZ LUQUE, Raul ; GUEGAN, Damien Bernard Emeric</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP4448933A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2024</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION 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>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>SOULAT, Laurent</creatorcontrib><creatorcontrib>SCHVALLINGER, Michaël Franck Antoine</creatorcontrib><creatorcontrib>SECONDAT DE MONTESQUIEU, Antoine Claude Baudouin</creatorcontrib><creatorcontrib>MARTINEZ LUQUE, Raul</creatorcontrib><creatorcontrib>GUEGAN, Damien Bernard Emeric</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SOULAT, Laurent</au><au>SCHVALLINGER, Michaël Franck Antoine</au><au>SECONDAT DE MONTESQUIEU, Antoine Claude Baudouin</au><au>MARTINEZ LUQUE, Raul</au><au>GUEGAN, Damien Bernard Emeric</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIRCRAFT TURBINE ENGINE</title><date>2024-10-23</date><risdate>2024</risdate><abstract>Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30) and configured to divide the primary airflow (18) into two to form the secondary air flows (20, 22); - first variable guide vanes (40) which are distributed around the shaft and each comprise a leading edge (40a) which is located upstream of the separator (24) and trailing edges (40b, 40c) which are located in the secondary airflows (20, 22); - and fixed guide vanes (42) which are distributed around the shaft in the external airflow and downstream of the first variable vanes (40).</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | AIRCRAFT TURBINE ENGINE |
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