A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

A bearing system including a frequency independent damper assembly and a bearing pad assembly. The damper assembly includes a housing, a plunger, a moving central post and a support spring. The plunger is movable within a housing to define a first primary damper cavity and a second primary damper cavity. The moving central post has defined therein a fluid channel for a pressurized working fluid flow. The support spring includes a plurality of flexible elements coupled to the housing and disposed radially outward of the first and second primary damper cavities. The support spring defines first and second accumulator cavity. A flow-through channel couples the first accumulator cavity to the second accumulator cavity. In an embodiment, the flow-through channel may be disposed within the moving central post. The bearing pad assembly includes a bearing pad including a plurality of bearing pad orifices coupled to the fluid channel in the moving central post.

An enclosure for a turbomachine includes a turbomachine drive shaft rotating about a longitudinal axis (X) by means of two roller bearings, an upstream bearing and a downstream bearing, each having an inner ring carried by the drive shaft. The two bearings share a single integral outer ring that has an upstream end and a downstream end connected to one another by a section of studs. The single outer ring is carried by an upstream base plate and a downstream base plate of a bearing support configured to be attached to a stationary structure of the turbomachine.

A turbocharger includes a variable nozzle disposed between a turbine housing and a bearing housing and a spring having an annular shape. The spring is disposed between the variable nozzle and the bearing housing, and is configured to generate a biasing force that biases the variable nozzle away from the bearing housing to widen a spacing between the variable nozzle and the bearing housing in a rotation axis direction. The spring includes an outer peripheral portion that applies the biasing force to the variable nozzle and an inner peripheral portion that comes into contact with the bearing housing. The outer peripheral portion of the spring is located further away from the turbine housing than the inner peripheral portion of the spring in the rotation axis direction.

A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

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.

A turbine exhaust unit supporting device that supports a turbine exhaust unit is provided. The turbine exhaust unit supporting device installed at a rear side of a turbine casing to support a turbine exhaust unit through which exhaust gas passing through a turbine is discharged, the supporting device includes a casing supporting block unit installed on an outer circumferential surface of the turbine casing, an exhaust unit supporting block unit spaced apart from the casing supporting block unit and installed on an outer circumferential surface of the turbine exhaust unit, and a rotary coupler including a first end rotatably coupled to the casing supporting block unit and a second end rotatably coupled to the exhaust unit supporting block unit.

An assembly for supporting and guiding a drive shaft for an aircraft turbine engine includes a bearing support having a cylindrical housing for receiving an outer ring of a bearing, and a device for rotationally retaining a first portion of the outer ring which is detached from its attachment to the bearing support. When the detachment occurs, the free outer peripheries of the first teeth of the first portion cooperate by wedge effect in the tangential direction with complementary inner surfaces of the housing of the bearing support and/or the free inner peripheries of the second teeth inside the housing cooperate by wedge effect in the tangential direction with complementary outer surfaces of the outer ring.

A gas turbine engine including a compressor that compresses air taken in; a combustor that sprays a fuel into the compressed air and combusts the fuel; a turbine rotated by energy of the combustion gas generated by the combustor; a rotating shaft coupling the compressor and the turbine; a rear bearing that is a cageless ball bearing including an inner race, an outer race, and a ball, the inner race being fixed to a portion of the rotating shaft which portion is close to the turbine; a housing to which the rear bearing is attached; and a rear bearing holding member that is interposed between the rear bearing and the housing and holds the outer race of the rear bearing such that the outer race of the rear bearing is movable in an axial direction relative to the housing.

A power transmission system for a turbine engine is provided. The power transmission system includes a transmission shaft that is connected to a drive shaft by bevel gears, and that drives equipment or accessories. The transmission shaft is designed to operate under supercritical conditions and includes a damper system for damping vibration at its resonant speed.