Fairing installations disclosed herein may include a damper for mitigating vibration of a cantilevered fairing disposed in a bypass duct of a gas turbine engine. The bypass duct may include a first shroud radially spaced apart from a second shroud to define a bypass passage between the first and second shrouds. The fairing may be disposed in the bypass passage and cantilevered from the first shroud. The fairing may have a secured end secured to the first shroud and a free end proximate the second shroud. The damper may be engaged with the free end of the fairing to damp movement of the free end of the fairing.

A gear baffle, a gearbox of a gas turbine engine including a gear baffle, and a method of installing a gear baffle adjacent to a gear in a gearbox of a gas turbine engine are disclosed. The gearbox includes a housing, having disposed therein a gear, and a baffle adjacent to the gear to interact with lubricant fluid around the gear. The baffle includes a first interface for attaching the baffle to a structure to a first side of the gear, and a second interface for attaching the baffle to a structure to a second, axially opposite, side of the gear. The second interface may be axially spaced apart from the first interface by an axial distance. The baffle may include a main wall interconnecting the first interface with the second interface. The main wall may include a compliant corrugation that accommodates a variation in the axial distance between the first interface and the second interface.

A centrifugal pump for conveying a fluid includes a housing having an inlet and an outlet for the fluid. An impeller is arranged in the housing for rotation in an axial direction to convey the fluid from the inlet to the outlet, a shaft extends in the axial direction for driving the impeller, and a stationary guide device for guiding the fluid from the impeller to the outlet is connected to the housing. A resilient compensating element is disposed between the housing and the guide device, is arranged around the shaft, and holds the guide device in a centered position to the impeller during a radial relative movement to the housing.

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

A variable guide vane (VGV) assembly for a gas turbine engine, has: variable guide vanes circumferentially distributed about a central axis, the variable guide vanes rotatable about respective spanwise axes; and a unison member rollingly engageable to a casing of the gas turbine engine for rotation about the central axis, the unison member operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, the unison member having: a first ring extending around the central axis, a second ring spaced apart from the first ring and extending around the central axis, and connecting members connecting the first ring to the second ring.

A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.

An air inlet manifold and a gas turbine including the same, capable of preventing transmission of vibration from the gas turbine to the air inlet manifold, while at the same time preventing air leakage, and the air inlet manifold is installed to be spaced apart from the compressor and relatively movable, as the anti-vibration pad in a compressed state is interposed between the air inlet manifold and the compressor.

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount pin assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mount pin assembly is configured to couple the seal segment to the carrier.

An exhaust nozzle of a gas turbine engine includes: a nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. One of the struts is connected to the wall by a coupling arrangement that includes two first brackets and a third bracket, the brackets being spaced in an axial direction and being connected either directly to the wall or to a sliding element that is arranged in a displaceable manner in the wall. The brackets each have a first, highest stiffness in a first direction and smaller stiffnesses in a second and third direction. The brackets are oriented such that with the two first brackets, the first direction is aligned with a circumferential direction of the nozzle and that with the third bracket, the first direction is aligned with the axial direction of the nozzle.

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.