A turbomachine of an aircraft comprising an outer casing delimiting with an inner hub, a flow path 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; and a second propeller downstream of the first propeller, the first propeller being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor, the second propeller being further disposed at a distance between 1.5 and 4 cord lengths from the first propeller defined between the respective axes of shimming of each of the first and second propellers.
Turbomachine with unducted dual propellers
2024-05-21
Patent
Electronic Resource
English
UNDUCTED RECTIFIER FOR A TURBOMACHINE, TURBOMACHINE MODULE AND AIRCRAFT TURBOMACHINE
European Patent Office | 2024
|Unducted rectifier for a turbomachine, turbomachine module and aircraft turbomachine
European Patent Office | 2025
|Pylon for fixing an aircraft engine having unducted pusher propellers
European Patent Office | 2017
|