A gas turbine engine and structure for mounting the gas turbine engine on an aircraft is disclosed. Techniques for controlling the magnitude of engine case deflection from the axis of the engine are developed. The transfer of a portion of the gust and thrust loads externally of the engine case to a location downstream of the rearward engine mount generates a reverse moment which counteracts deflection in the engine case.
An aircraft gas turbine engine of the type having an engine case and including forward mounting means and rearward mounting means for attaching the engine case to the aircraft, wherein the improvement comprises: means external to the engine case and pivotable about the forward mounting means for transferring loads applied about the forward mounting means to a location on the engine case downstream of the second mounting means. An aircraft gas turbine engine of the turbofan type having a fan section and a core section wherein the core section is circumscr...
이 특허를 인용한 특허 피인용횟수: 17
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