Abstract: According to an aspect, a system includes a memory system configured to store a plurality of instructions and a processing system. The processing system is configured to communicate with the memory system and execute the instructions that result in determining an initial torque applied to a component stack, determining an assembly torque and an angle of turn applied to the component stack after the initial torque is applied, and determining a friction value associated with the component stack. Execution of the instructions further result in determining a stack load of the component stack based on the friction value, the assembly torque, and the angle of turn, and outputting an indicator of the stack load.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft configured to rotate during operation of the gas turbine engine, and a squeeze film damper radially outside the shaft. The squeeze film damper includes a cavity including a film of lubricant axially between first and second cavity seals, and further includes a reservoir fluidly coupled to the cavity. A method is also disclosed.

Abstract: A contacting seal for a gas turbine engine include a seal element rotationally fixed relative to an axis of rotation, and a seal seat configured to rotate circumferentially about an axis of rotation and contact the seal element at an interface surface of the seal seat. The seal seat includes an interface component including a seat wall including the interface surface and a seat cavity surface opposite the interface surface, such that a wall thickness of the interface component is defined therebetween. A cover component is secured to the interface component, the cover component including a cover cavity surface. The seat cavity surface and the cover cavity surface define a cooling cavity therebetween configured such that a flow of fluid therethrough cools the interface component via contact between the coolant and the seat cavity surface.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft configured to rotate during operation of the gas turbine engine, and a squeeze film damper radially outside the shaft. The squeeze film damper includes a cavity including a film of lubricant axially between first and second cavity seals, and further includes a reservoir fluidly coupled to the cavity. A method is also disclosed.

Abstract: A contacting seal for a gas turbine engine include a seal element rotationally fixed relative to an axis of rotation, and a seal seat configured to rotate circumferentially about an axis of rotation and contact the seal element at an interface surface of the seal seat. The seal seat includes an interface component including a seat wall including the interface surface and a seat cavity surface opposite the interface surface, such that a wall thickness of the interface component is defined therebetween. A cover component is secured to the interface component, the cover component including a cover cavity surface. The seat cavity surface and the cover cavity surface define a cooling cavity therebetween configured such that a flow of fluid therethrough cools the interface component via contact between the coolant and the seat cavity surface.

Abstract: The present disclosure relates to shock mounts for turbine engine components. A shock mount may be used to mount an accessory gearbox to an engine case. The shock mount may allow free thermal expansion, while providing damping and stiffness in response to vibrations. The shock mount may include a cylinder filled with fluid, and a piston telescopically moveable within the cylinder. The piston may be coupled to an orifice plate. The orifice plate may include orifices through which the fluid may flow in response to compression or extension of the shock mount. The interaction of the fluid and the orifice plate may resist rapid compression or extension of the shock mount while allowing relatively slow compression or extension of the shock mount.

Abstract: The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counter-clockwise.

Abstract: The present disclosure relates to shock mounts for turbine engine components. A shock mount may be used to mount an accessory gearbox to an engine case. The shock mount may allow free thermal expansion, while providing damping and stiffness in response to vibrations. The shock mount may include a cylinder filled with fluid, and a piston telescopically moveable within the cylinder. The piston may be coupled to an orifice plate. The orifice plate may include orifices through which the fluid may flow in response to compression or extension of the shock mount. The interaction of the fluid and the orifice plate may resist rapid compression or extension of the shock mount while allowing relatively slow compression or extension of the shock mount.

Abstract: The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counter-clockwise.

Abstract: A bearing support for a rotor of an aircraft turbine engine includes a frangible linkage designed to enable the engine to safely shut down despite the introduction of an excessive unbalance to the fan stage.