Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure, a bearing and a gearbox. The rotating structure is configured to rotate about a rotational axis. The rotating structure includes a shaft and a bladed rotor connected to the shaft. The stationary structure circumscribes the rotating structure. The bearing rotatably mounts the shaft to the stationary structure. The gearbox is disposed radially inboard of the bearing.

Abstract: A gas turbine engine has a shaft having an inner diameter surface. A plug is mounted in the shaft. An oil nozzle is positioned to direct a flow of oil to an interior of the shaft. The plug has: a first section; a second section having an outer diameter periphery; and an axial gap between the first section and the second section.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes an electric machine, a turbine engine component and a lubrication system. The electric machine includes a rotor and a stator. The turbine engine component is discrete from the electric machine. The lubrication system includes a first lubricant circuit, a second lubricant circuit and a lubricant source fluidly coupled in parallel with the first lubricant circuit and the second lubricant circuit. The first lubricant circuit includes a machine volume for the electric machine. The second lubricant circuit includes a component volume for the turbine engine component.

Abstract: A seal assembly for a turbine engine extends along a center axis and includes a seal support and a seal carrier configured to translate relative the seal support. A seal is connected to the seal carrier and a spring is disposed between the seal support and the seal carrier. A spring carrier is disposed between the spring and the seal support. A first end of the spring is connected to the spring carrier and the spring carrier is connected to the seal support. The spring includes a second end disposed opposite the first end of the spring. The second end of the spring contacts the annular seal carrier.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure, a bearing and a gearbox. The rotating structure is configured to rotate about a rotational axis. The rotating structure includes a shaft and a bladed rotor connected to the shaft. The stationary structure circumscribes the rotating structure. The bearing rotatably mounts the shaft to the stationary structure. The gearbox is disposed radially inboard of the bearing.

Abstract: 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.

Abstract: 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.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes an electric machine, a turbine engine component and a lubrication system. The electric machine includes a rotor and a stator. The turbine engine component is discrete from the electric machine. The lubrication system includes a first lubricant circuit, a second lubricant circuit and a lubricant source fluidly coupled in parallel with the first lubricant circuit and the second lubricant circuit. The first lubricant circuit includes a machine volume for the electric machine. The second lubricant circuit includes a component volume for the turbine engine component.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure and an electric machine. The rotating structure is configured to rotate about a rotational axis. The stationary structure circumscribes the rotating structure. The electric machine includes a rotor and a stator. The rotor circumscribes the rotating structure and is coupled to the rotating structure through a spline connection. The stator is connected to the stationary structure.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine shaft, a gearbox and a coupler. The turbine engine shaft is configured to rotate about a rotational axis. The gearbox includes a gear configured to rotate about the rotational axis. The coupler is coupled to the turbine engine shaft by a coupler-shaft connection. The coupler-shaft connection is configured as or otherwise includes a crowned spline connection. The coupler is coupled to the gear by a coupler-gear connection. The coupler-gear connection is configured as or otherwise includes a crowned spline connection.

Abstract: A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.

Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

Abstract: A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.

Abstract: A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.

Abstract: A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.

Abstract: A contacting seal for a gas turbine engine includes a seal seat configured to rotate circumferentially about an axis of rotation and a seal element configured to contact the seal seat at an interface surface. The seal element is rotationally fixed relative to the axis of rotation. An actively-controlled actuation system is operably connected to the seal element to control a contact force between the seal element and the seal seat at the interface surface based on a level of lubricant flow to the interface surface. A method of operating a contacting seal includes positioning a rotationally fixed seal element in contact with a rotating seal seat at an interface surface between the seal seat and the seal element, and actively-controlling a contact pressure between the seal seat and the seal element at the interface surface utilizing an actuation system.

Abstract: A seal assembly for a turbine engine extends along a center axis and includes a seal support and a seal carrier configured to translate relative the seal support. A seal is connected to the seal carrier and a spring is disposed between the seal support and the seal carrier. A spring carrier is disposed between the spring and the seal support. A first end of the spring is connected to the spring carrier and the spring carrier is connected to the seal support. The spring includes a second end disposed opposite the first end of the spring. The second end of the spring contacts the annular seal carrier.

Abstract: A contacting seal for a gas turbine engine includes a seal seat configured to rotate circumferentially about an axis of rotation and a seal element configured to contact the seal seat at an interface surface. The seal element is rotationally fixed relative to the axis of rotation. An actively-controlled actuation system is operably connected to the seal element to control a contact force between the seal element and the seal seat at the interface surface based on a level of lubricant flow to the interface surface. A method of operating a contacting seal includes positioning a rotationally fixed seal element in contact with a rotating seal seat at an interface surface between the seal seat and the seal element, and actively-controlling a contact pressure between the seal seat and the seal element at the interface surface utilizing an actuation system.

Abstract: A seal assembly for a turbine engine extends along a center axis and includes a seal support and a seal carrier configured to translate relative the seal support. A seal is connected to the seal carrier and a spring is disposed between the seal support and the seal carrier. A spring carrier is disposed between the spring and the seal support. A first end of the spring is connected to the spring carrier and the spring carrier is connected to the seal support. The spring includes a second end disposed opposite the first end of the spring. The second end of the spring contacts the annular seal carrier.