A mounting assembly includes an engine mount link, an engine mount block, a fusible component, and a catcher component. The engine mount block is connected to a pylon and the engine mount link. The fusible component and the catcher component have respective first and second shear strengths. The catcher component is disposed within a catcher aperture. When an applied shear stress on the fusible component is less than the first shear strength, the engine mount link is stationary with respect to the engine mount block. When the applied shear stress on the fusible component exceeds the first shear strength, the fusible component mechanically fails and causes the catcher component to move relative to the catcher aperture further causing a corresponding movement of the engine mount link.
MOUNTING ASSEMBLY FOR GAS TURBINE ENGINE
25.07.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Assembly for mounting a turbine engine to an airframe
Europäisches Patentamt | 2019
|Assembly comprising aircraft turbine engine and mounting pylon therefor
Europäisches Patentamt | 2023
|