A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.

A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.

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.

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.

A structural subassembly which has a bearing which comprises a statically arranged outer ring and a rotatably arranged inner ring, wherein the inner ring is connected for conjoint rotation to a component that is rotatable about a longitudinal axis or said inner ring forms part of such a component, and wherein the longitudinal axis defines an axial direction of the bearing. The structural subassembly furthermore comprises a housing flange of a support structure, to which flange the statically arranged outer ring is connected. Provision is made for the outer ring to be of two-part design, wherein each part of the outer ring has a connecting element which is connected to the housing flange, wherein the housing flange is arranged between the two connecting elements in the axial direction.

Provided are a journal bearing and a rotary machine, including: a housing that has an annular shape and is disposed around a rotating shaft; a plurality of bearing pads that are disposed between the housing and the rotating shaft to be spaced from each other at predetermined intervals in the circumferential direction of the housing; and a support that supports at least one end of each bearing pad in the axial direction of the rotating shaft to allow the each bearing pad to swing in the housing about an axis serving as a fulcrum in parallel to the axial direction.

An assembly is provided for a turbine engine. This turbine engine assembly includes a first rotating structure, a turbine engine apparatus, a rotating coupler and a seal assembly. The first rotating structure is configured to rotate about a rotational axis. The turbine engine apparatus includes an electric machine and a second rotating structure. The electric machine includes an electric machine rotor and an electric machine stator. The second rotating structure is configured to rotate about the rotational axis and is coupled to the electric machine rotor. The rotating coupler is coupled to the first rotating structure by a first connection. The rotating coupler is coupled to the second rotating structure by a second connection. The seal assembly includes a rotating seal land and a stationary seal element. The rotating seal land is mounted onto the rotating coupler. The stationary seal element sealingly engages the rotating seal land.

An assembly is provided for a turbine engine. This turbine engine assembly includes a first rotating structure, a turbine engine apparatus, a rotating coupler and a seal assembly. The first rotating structure is configured to rotate about a rotational axis. The turbine engine apparatus includes an electric machine and a second rotating structure. The electric machine includes an electric machine rotor and an electric machine stator. The second rotating structure is configured to rotate about the rotational axis and is coupled to the electric machine rotor. The rotating coupler is coupled to the first rotating structure by a first connection. The rotating coupler is coupled to the second rotating structure by a second connection. The seal assembly includes a rotating seal land and a stationary seal element. The rotating seal land is mounted onto the rotating coupler. The stationary seal element sealingly engages the rotating seal land.

An assembly is provided for a turbine engine. This turbine engine assembly includes a stationary structure, a rotating structure and an electric machine. The rotating structure is rotatably mounted to the stationary structure by a first bearing and a second bearing. The electric machine is between the first bearing and the second bearing. The electric machine includes a rotor and a stator circumscribing the rotor. The rotor is connected to the rotating structure. The stator is connected to the stationary structure.