A propulsion assembly (100) for an aircraft, in particular a multi-engine helicopter, comprising: at least one first engine (1) and a second engine (2) configured to operate in at least one standby mode; a main air circulation device (30) configured to drain air from the first engine (1) via a first drain channel (310) and/or from the second engine (2) via a second drain channel (320) to deliver air to the apparatus of the propulsion assembly (100); and a secondary air circulation device (40) configured to discharge air from the other of the first or second engines (1, 2) that is not operating in the standby mode when the first or second engines (1, 2) are operating in the standby mode, and to deliver the air to the one of the first or second engines (1, 2) that is operating in the standby mode.

    推进组件(100),其用于飞行器、特别是多发动机直升机,包括:至少一个第一发动机(1)和第二发动机(2),构造成在至少一个待机模式下运行;主空气循环装置(30),构造成经由第一引放通道(310)从第一发动机(1)引放空气,并且/或者经由第二引放通道(320)从第二发动机(2)引放空气,以将空气运送到推进组件(100)的设备;以及副空气循环装置(40),构造成当第一发动机或第二发动机(1、2)在待机模式下运行时从第一发动机或第二发动机(1、2)中的未在待机模式下运行的另一个引放空气,并将该空气运送到第一发动机或第二发动机(1、2)中的在待机模式下运行的一个。


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    Titel :

    Improved propulsion assembly for multi-engine aircraft


    Weitere Titelangaben:

    用于多发动机飞行器的改进推进组件


    Beteiligte:

    Erscheinungsdatum :

    18.02.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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