A gas turbine engine (10) for an aircraft includes a fan system. The fan system has a reverse traveling wave first flap mode, fan RTW, and comprises: a fan (23) located upstream of the engine core; and a fan shaft (36); and a front engine structure (42) arranged to support the fan shaft (36) and having front engine structure nodding modes including a pair of modes at similar but unequal natural frequencies in orthogonal directions; and a gearbox (30). The engine further includes the fan system (23, 36) and a gearbox output shaft (35) arranged to drive the fan shaft (36) having a first reverse swirling rotor dynamic mode, i.e. Rotor RW and a first forward swirling rotor dynamic mode 1FW. The engine (10) has a maximum takeoff speed (MTO). The mutual frequency margin of the following formula is in the range of 5% to 50%.

    一种用于飞行器的气体涡轮引擎(10)包括风扇系统,该风扇系统具有逆向行波第一襟翼模式、即风扇RTW,并且包括:风扇(23),其位于引擎核心的上游;和风扇轴(36);和前引擎结构(42),其布置为支撑风扇轴(36)并具有前引擎结构点头模式,该前引擎结构点头模式包括在正交方向上处于类似但不相等的固有频率的一对模式;和齿轮箱(30)。包括风扇系统(23、36)和布置成驱动风扇轴(36)的齿轮箱输出轴(35)的LP转子系统具有第一逆向涡动转子动态模式、即转子RW和第一正向涡动转子动态模式1FW。引擎(10)具有最大起飞速度MTO。下述公式的互相频率裕度在5%到50%的范围内:


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    Title :

    Aircraft engine with improved vibration mode handling


    Additional title:

    具有改进的振动模式处理的飞行器引擎


    Contributors:

    Publication date :

    2021-12-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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