TURBOMACHINE WITH UNDUCTED DUAL PROPELLERS
The invention relates to a turbomachine of an aircraft comprising an outer casing (2) delimiting with an inner hub (3), a flow path (1) of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of...
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| creator | TANTOT, Nicolas Jérôme Jean LAMBEY, Mario Antoine BINDER, Anthony |
| description | The invention relates to a turbomachine of an aircraft comprising an outer casing (2) delimiting with an inner hub (3), a flow path (1) of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers. |
| format | Patent |
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said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers.</description><language>eng</language><subject>AEROPLANES ; AIR INTAKES FOR JET-PROPULSION PLANTS ; AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; BLASTING ; COMBUSTION ENGINES ; COMBUSTION ENGINES IN GENERAL ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; COSMONAUTICS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GAS-TURBINE PLANTS ; HEATING ; HELICOPTERS ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; 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said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers.</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>COMBUSTION ENGINES IN GENERAL</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>COSMONAUTICS</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>INTERNAL-COMBUSTION PISTON ENGINES</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNAKCQ1y8vd1dPbw9HNVCPcM8VAI9XMJdQ5xdVFwCXX0UQgI8g9w9fFxDQrmYWBNS8wpTuWF0twMym6uIc4euqkF-fGpxQWJyal5qSXxocFGBkaGJgbGhmaWjobGxKkCAPvVJcQ</recordid><startdate>20211230</startdate><enddate>20211230</enddate><creator>TANTOT, Nicolas Jérôme Jean</creator><creator>LAMBEY, Mario Antoine</creator><creator>BINDER, Anthony</creator><scope>EVB</scope></search><sort><creationdate>20211230</creationdate><title>TURBOMACHINE WITH UNDUCTED DUAL PROPELLERS</title><author>TANTOT, Nicolas Jérôme Jean ; LAMBEY, Mario Antoine ; BINDER, Anthony</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2021403169A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2021</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>COMBUSTION ENGINES IN GENERAL</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>COSMONAUTICS</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>INTERNAL-COMBUSTION PISTON ENGINES</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>TANTOT, Nicolas Jérôme Jean</creatorcontrib><creatorcontrib>LAMBEY, Mario Antoine</creatorcontrib><creatorcontrib>BINDER, Anthony</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>TANTOT, Nicolas Jérôme Jean</au><au>LAMBEY, Mario Antoine</au><au>BINDER, Anthony</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBOMACHINE WITH UNDUCTED DUAL PROPELLERS</title><date>2021-12-30</date><risdate>2021</risdate><abstract>The invention relates to a turbomachine of an aircraft comprising an outer casing (2) delimiting with an inner hub (3), a flow path (1) of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers.</abstract><oa>free_for_read</oa></addata></record> |
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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 COMBUSTION ENGINES IN GENERAL CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INTERNAL-COMBUSTION PISTON ENGINES LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS |
| title | TURBOMACHINE WITH UNDUCTED DUAL PROPELLERS |
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