This application relates generally to connectors and, more particularly, to connectors sized to receive a threaded apparatus.
Aircraft engines typically include a plurality of threaded connections that are torqued during assembly. For example, an aircraft engine may be mounted to an aircraft at various locations, such as on a wing, to a fuselage, or to a tail. The engine is typically mounted at a forward and an aft end with a mounting system that includes a plurality of thrust links including connectors at each end. The connectors include openings extending therethrough that are defined by substantially planar inner surfaces including a plurality of threads.
The thrust link connectors are exposed to potential vibrational stresses that are induced during engine operation. To minimize the effect of exposure to such vibrational stresses, threaded components are torqued. When threaded components are loaded by torque or an external load, stresses are induced within the connectors. A highest stress area typically occurs in a first thread. More specifically, a highest stress is induced into a first thread root fillet that is defined between the first thread and a subsequent thread. Continued exposure to such stresses, may weaken the first thread and reduce a low cycle fatigue capability of the threaded connection. Prolonged reduced low cycle fatigue may shorten a useful life of the threaded connection.
To facilitate improving the low cycle fatigue capability of threaded connections, the threads of at least some known threaded components are rolled to provide a surface that is pre-stressed in compression. Such a process is time-consuming. In some other known applications, thread rolling is not available and the threads are instead cut back to facilitate improving low cycle fatigue capability. However, such connections are also costly and time consuming to manufacture.