In conventional aircraft design, engine loads are transferred directly from the engine core and fan case to the pylon via engine mounts. Literature is available on the modeling of individual powerplant components, but limited work is available on the whole assembled system (engine, pylon, and nacelle). The influence of the structural connections between the components on overall system performance has not been investigated. Herein, a finite element model is described and can be used to assess connection strategies between powerplant components and if such arrangements can effectively enhance engine performance by reducing detrimental engine structural deformations (engine carcass bending, rotation, and ovalization). The method is demonstrated for a generic high bypass ratio engine design, focusing on connections between the engine and thrust reverser unit. The method identifies a modified attachment scheme between the engine rear turbine casing and the inner barrel of the thrust reverser unit, which reduces engine deformations across multiple loading scenarios. Maximum reductions of 97 and 96% have been observed in carcass bending and ovalization, respectively.

在传统的飞机设计中，发动机负载通过发动机支座直接从发动机核心和风扇箱传递到吊架。有关单个动力装置部件建模的文献可用，但整个组装系统（发动机，吊架和机舱）的工作量有限。尚未研究组件之间的结构连接对整体系统性能的影响。在此，描述了有限元模型，该模型可用于评估动力装置部件之间的连接策略，以及这种布置是否可以通过减少有害的发动机结构变形（发动机胎体弯曲，旋转和椭圆化）有效地增强发动机性能。该方法已针对通用的高旁路比发动机设计进行了演示，着重于发动机与反推力装置之间的连接。该方法确定了发动机后涡轮机壳体与推力反向器单元内筒之间的改进附接方案，该方案可在多种载荷情况下减少发动机变形。car体弯曲和椭圆化分别观察到最大减少量为97％和96％。