A jig for assembling and extracting a blade root spring for fixing a rotor blade to a rotor includes: an extrusion mechanism for extruding the blade root spring or an extrusion rod pressed against the blade root spring; and a base plate to which the extrusion mechanism is fixed. The base plate is formed with a first groove for receiving a reaction force which is obtained when the extrusion mechanism extrudes the extrusion rod toward the blade root spring to extrude and assemble the blade root spring or to extract the blade root spring.

A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

A lift assembly includes an upper rail. A plurality of rail flanges extend from the upper rail. The lift assembly further includes a plurality of combustion can support assemblies spaced apart from one another. Each combustion can support assembly of the plurality of combustion can support assemblies includes a support flange slidably coupled to a rail flange of the plurality of rail flanges, an outer sleeve, and an inner sleeve assembly configured to removably couple to a combustion can of the turbomachine. Each combustion can support assembly of the plurality of combustion can support assemblies defines a cylindrical coordinate system having an axial direction, a radial direction, and a circumferential direction. Each combustion can support assembly of the plurality of support assemblies is configured to move along any of the axial direction, the radial direction, or the circumferential direction relative to the upper rail.

A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard axial compressor stages. Each axial compressor stage included in the set of standard axial compressor stages includes a rotor having a plurality of blades configured to rotate about an axis and a stator having a plurality of stator vanes.

A turbine assembly for a turbocharger and method of assembling is disclosed. The turbine assembly may comprise a turbine wheel coupled to a rotatable turbocharger shaft, and a turbine housing that at least partially encloses the turbine wheel. The turbine housing may include an exhaust diffuser configured to direct a flow of exhaust, a support member coupled to the exhaust diffuser by a clamp assembly, the clamp assembly, a diffuser gap and a support gap. The clamp assembly may be disposed on the exhaust diffuser and on the support member. The clamp assembly includes a containment ring and a clamp plate. The containment ring may include a channel. The clamp plate may be disposed in the channel. The diffuser gap may be disposed between the containment ring and the exhaust diffuser. The support gap may be disposed between the containment ring and the support member.

A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.

An exhaust duct for an engine includes an outer exhaust duct and a nested exhaust duct capable of having at least two configurations. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a first length of the nested exhaust duct in a first configuration. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a second length of the nested exhaust duct in a second configuration, which is less than the first length.

An adjustable mount for an aircraft engine accessory. A first bracket adapted to be coupled to the engine accessory has a first bore with a first annular bushing with a threaded radially inner surface extending through the first bore. A second bracket operatively coupled to the engine at mounting location has a second bore with a second annular bushing with a threaded radially inner surface extending through the second bore. A threaded stud extends axially through the first and second bushings and is engaged with their threaded inner surfaces. Rotation of the first and/or second bushings varies the relative axial positions of the first and second bushings on the stud, thereby adjusting an axial gap between first and second brackets. First and second nuts fastened to first and second ends of the threaded stud axially retain the mount together with the axial gap between the first and second brackets fixed.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate, a second side plate and a backing plate that extend circumferentially about an assembly axis. A first brush seal and a second brush seal are positioned on opposite sides of the backing plate such that the first brush seal is between the first side plate and the backing plate and such that the second brush seal is between the second side plate and the backing plate. The first brush seal is dimensioned to establish a first sealing relationship with a first gas turbine engine component. The second brush seal is dimensioned to establish a second sealing relationship with a second gas turbine engine component. A method of assembly is also disclosed.