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首页> 外文会议>International Congress on Sound and Vibration >NUMERICAL MODEL OF AIRCRAFT GAS TURBINE ENGINE (BASED ON EXPERIMENTAL DATA OF DYNAMICAL COMPLIANCES OF ENGINE BODY)
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NUMERICAL MODEL OF AIRCRAFT GAS TURBINE ENGINE (BASED ON EXPERIMENTAL DATA OF DYNAMICAL COMPLIANCES OF ENGINE BODY)

机译：航空器燃气发动机的数值模型（基于发动机体型动力学提供的实验数据）

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Compliance of aircraft to new noise standards defines the tendency to switch to extra-high bypass ratio engines (from 4…6 to 8…11). The introduction of high bypass ratio engines has caused broadening of the spectrum of power plant vibration impact and increase of structure-borne noise contribution to the acoustic field of the pressurized cabin. Facilities for reduction engine vibration intensity and vibration transfer along structure come first by selecting of vibration protection for pressurized cabin and integration vibration protection units into engine mounting attachments seems to us the most effective. But whatever vibration protection means are used to select parameters of vibration isolation units, calculated model is required which is based on real dynamic characteristics of engines and airframe in mounting points. The long-term investigations directed to dynamical characteristics definition for number of engines bodies (with different by-pass ratio) and airframe design of airliner allow to significantly specify calculation models of advanced aircraft design constructions in engine's rotor frequency range. And it allows to define tendency of engine's dynamic characteristics variation with by-pass ratio increasing. Analysis of experimental data makes it possible to divide the frequency range of investigation into several sub-ranges characterized by certain dynamic behavior of the engine and com be presented by simple and clear mathematical model. Taking this into account the analytical function was found, which describes change of engine compliances frequency characteristics. Within a wide range of rotor frequencies the dynamic behavior of engine body corresponds to the model of elastic-inertial system or to an elastic-dissipative element. It differs substantially from the idealized rigid-body model of aircraft gas turbine engine both by the value of dynamic compliance module and by the type of dynamic behavior.
机译：飞机对新噪声标准的符合定义了切换到超高旁路比率发动机的趋势（从4 ... 6到8 ... 11）。高旁通比发动机引入引发了扩大电厂振动频谱的频谱，以及对加压舱的声场的结构传播噪声贡献的增加。通过选择加压舱和集成振动保护单元的振动保护，首先通过选择加压舱和整体振动保护单元来实现沿着结构的振动强度和振动转移。但是，无论使用什么振动保护装置选择振动隔离单元的参数，都需要计算的模型，基于安装点中的发动机和机身的实际动态特性。涉及用于发动机体的数目动态特性定义（具有不同的旁通比）和客机的机身设计的长期研究允许发动机的转子的频率范围内显著指定的先进飞机的设计构造的计算模型。并且它允许定义发动机的动态特性随旁路比率变化的倾向。实验数据的分析使得可以将调查的频率范围分为几个子范围，其特征在于通过简单明确的数学模型呈现的发动机和COM的某些动态行为。考虑到这一点，发现了分析功能，其描述了发动机的变化率频率特性。在各种转子频率内，发动机主体的动态行为对应于弹性惯性系统的模型或弹性耗散元件。它基本上不同于飞机燃气轮机发动机的理想化刚体模型，这两者都是动态合规模块的价值和动态行为的类型。

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