Abstract: An assembly of a rotating component and a rotationally stationary component includes a first bearing portion located at the rotating component and rotatable therewith, and a second bearing portion located at the rotationally stationary component. The second bearing portion is supported at the rotationally stationary component and rotatably with the rotating component when in contact with the first bearing portion. The first bearing portion and the second bearing portion define a single point contact therebetween.

Abstract: An assembly of a rotating component and a rotationally stationary component includes a first bearing portion located at the rotating component and rotatable therewith, and a second bearing portion located at the rotationally stationary component. The second bearing portion is supported at the rotationally stationary component and rotatably with the rotating component when in contact with the first bearing portion. The first bearing portion and the second bearing portion define a single point contact therebetween.

Abstract: A compressor assembly of a gas turbine engine includes a case including at least one opening and a stator assembly supported within the case. A lug assembly is secured to the case and sets a position of the stator assembly relative to the case. The lug assembly includes a lug engaging the stator assembly and a boss extending from the lug through the opening in the case. The boss including a threaded hole receiving a threaded member holding the lug assembly to the case and defines a seat for the threaded member that is spaced apart from an outer surface of the case.

Abstract: A bowed rotor prevention system for a gas turbine engine is provided. The bowed rotor prevention system includes a thermoelectric generator system operable to produce electricity from waste heat of the gas turbine engine. The bowed rotor prevention system also includes a bowed rotor prevention motor operable to drive rotation of turbomachinery of the gas turbine engine using the electricity produced by the thermoelectric generator system.

Abstract: A stator damper is disclosed. The stator damper has a body section and a damper finger. The body section rests against a stator assembly and a portion of each damper finger rests against a compressor casing. The stator damper is radially compressed between the stator assembly and the compressor casing. Thus, the stator damper exerts a radial force against the stator assembly. In this manner, relative motion of the stator assembly is damped.

Abstract: A stator assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, at least one stator vane including a platform, a seal member connected to the platform, and a damper between the platform and the seal member. The damper includes a plurality of first fingers and a plurality of second fingers, which are provided in an alternating arrangement.

Abstract: A bowed rotor prevention system for a gas turbine engine is provided. The bowed rotor prevention system includes a thermoelectric generator system operable to produce electricity from waste heat of the gas turbine engine. The bowed rotor prevention system also includes a bowed rotor prevention motor operable to drive rotation of turbomachinery of the gas turbine engine using the electricity produced by the thermoelectric generator system.

Abstract: A stator damper is disclosed. The stator damper has a body section and a damper finger. The body section rests against a stator assembly and a portion of each damper finger rests against a compressor casing. The stator damper is radially compressed between the stator assembly and the compressor casing. Thus, the stator damper exerts a radial force against the stator assembly. In this manner, relative motion of the stator assembly is damped.

Abstract: A stator assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, at least one stator vane including a platform, a seal member connected to the platform, and a damper between the platform and the seal member. The damper includes a plurality of first fingers and a plurality of second fingers, which are provided in an alternating arrangement.

Abstract: A compliant assembly includes an airfoil and a platform section from which the airfoil extends. The platform section includes a compliant attachment that is configured to secure the platform section to another structure different than the airfoil. The compliant attachment includes a compliant material.

Abstract: A variable vane damping assembly includes an inner bushing and an outer bushing. The inner bushing comprises an elastomeric material.

Abstract: A variable vane assembly includes a damper positioned between a platform and a trunnion. The damper is comprised of a resilient material.

Abstract: A variable vane includes a variable vane body that has an airfoil portion. The variable vane body is formed of a first material. A trunnion is attached at one end of the variable vane body. The trunnion includes a pivot formed of a second, different material.

Abstract: A stator vane assembly includes a vane having an inner end. In one example, the vane is aluminum. An inner shroud has an aperture receiving the inner end. A flexible material secures the inner end to the inner shroud. The material has an inner surface opposite the vane providing a seal land in one example. The inner shroud provides an arcuate inner shroud segment, which is constructed either cast aluminum or stamped sheet steel. An inner shroud segment has an arcuate wall providing multiple apertures, for example. First and second flanges are integral with and extending radially inwardly from a concave side of the wall.

Abstract: A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.

Abstract: An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots and positioned radially outward from the ID shroud. A plurality of stator airfoils extend from the ID shroud to the OD shroud. Each of the stator airfoils is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A bumper is positioned proximate a first end of each of the stator airfoils so as to limit movement of the stator airfoils in a radial direction.

Abstract: A variable vane includes a variable vane body that has an airfoil portion. The variable vane body is formed of a first material. A trunnion is attached at one end of the variable vane body. The trunnion includes a pivot formed of a second, different material.

Abstract: A compressor assembly of a gas turbine engine includes a case including at least one opening and a stator assembly supported within the case. A lug assembly is secured to the case and sets a position of the stator assembly relative to the case. The lug assembly includes a lug engaging the stator assembly and a boss extending from the lug through the opening in the case. The boss including a threaded hole receiving a threaded member holding the lug assembly to the case and defines a seat for the threaded member that is spaced apart from an outer surface of the case.

Abstract: A compliant assembly includes an airfoil and a platform section from which the airfoil extends. The platform section includes a compliant attachment that is configured to secure the platform section to another structure different than the airfoil. The compliant attachment includes a compliant material.

Abstract: An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots and positioned radially outward from the ID shroud. A plurality of stator airfoils extend from the ID shroud to the OD shroud. Each of the stator airfoils is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A bumper is positioned proximate a first end of each of the stator airfoils so as to limit movement of the stator airfoils in a radial direction.