Abstract: A dual-bearing assembly includes an annular cantilever beam spring positioned in-line and either internal or external to a pair of bearings. The spring includes first and second sets of N stand-offs evenly positioned around opposing top and bottom surfaces of a flat annular beam at 360/N degree intervals and angularly offset with respect to each other by 360/2N degrees such that each said stand-off is evenly spaced between adjacent pairs of stand-offs on the opposing surface. A pre-load mechanism is configured to apply opposing axial loads to the stand-offs to deflect the flat annular beam axially at each stand-off in opposing directions to induce a curvature to the annular beam and store energy in the beam to form load paths through the spring and rolling elements to pre-load the dual-bearing assembly. The dual-bearing assembly may be configured as DB, DF, universal or tandem.

Abstract: An annular cantilever beam spring is capable of exhibiting low friction and hysteresis and stiffness and specifically stiffness/volume far exceeding currently available COTS springs. The spring includes first and second sets of N stand-offs evenly positioned around opposing top and bottom surfaces of a flat annular beam at 360/N degree intervals and angularly offset with respect to each other by 360/2N degrees such that each said stand-off is evenly spaced between adjacent pairs of stand-offs on the opposing surface. The first and second sets of stand-offs are responsive to opposing axial loads to deflect the flat annular beam axially at each stand-off in opposing directions to induce a curvature to the annular beam and store energy in the beam. The spring stiffness is determined by the elastic material properties of the flat annular beam, not the initial geometry as is common with the COTS springs.

Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to the second end-of-cluster vane at an interface that includes an angled load interface therebetween; and a multiple of base vanes between the first end-of-cluster vane and the neighbor vane, the angled load interface different than an interface between each of the multiple of base vane.

Abstract: A gas turbine engine includes a first case, a second case, and a fastener. The first case has a first flange defining a first opening. The second case has a second flange defining a second opening. The second flange abuts the first flange. The fastener extends through the first opening and the second opening. The fastener defines a first bore that extends through a fastener head along an axis towards an outlet port defined by a fastener shank.

Abstract: An alignment tie rod device for connecting multiple components from generally opposite directions includes a shaft extending along a centerline. A first structure of the device includes opposing first and second rims and a base portion spanning between the rims. The base portion and rims define a channel that extends substantially normal to the centerline. A hole in the base portion is centered between the rims and communicates through the base portion for receipt of the shaft. An anti-rotation feature disposed operably within the channel is rigidly engaged to and projects radially outward from the shaft in diametrically opposed direction. The feature has diametrically opposite, arcuate, edges each having a radius of curvature that is substantially greater than a distance measured between the rims.

Abstract: A blade outer air seal according to an example of the present disclosure includes a seal body extending circumferentially about an axis and including at least one channel having a substantially solid radially outer surface. A substrate is radially inward of the at least one channel with respect to the axis. The substrate and the at least one channel form at least one cavity. A rotor rub strip is radially inward of the substrate.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Abstract: A probe assembly for a gas turbine engine is disclosed. The probe assembly may include a probe, and a fastener to retain the probe within a case of the gas turbine engine, the fastener including a sealing arrangement with a heat shield of the gas turbine engine.

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.

Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.

Abstract: A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion. A compressor section and a gas turbine engine including the heat shield are also disclosed.

Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment.

Abstract: An alignment tie rod device for connecting multiple components from generally opposite directions includes a shaft extending along a centerline. A first structure of the device includes opposing first and second rims and a base portion spanning between the rims. The base portion and rims define a channel that extends substantially normal to the centerline. A hole in the base portion is centered between the rims and communicates through the base portion for receipt of the shaft. An anti-rotation feature disposed operably within the channel is rigidly engaged to and projects radially outward from the shaft in diametrically opposed direction. The feature has diametrically opposite, arcuate, edges each having a radius of curvature that is substantially greater than a distance measured between the rims.

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 gas turbine engine includes a first case, a second case, and a fastener. The first case has a first flange defining a first opening. The second case has a second flange defining a second opening. The second flange abuts the first flange. The fastener extends through the first opening and the second opening. The fastener defines a first bore that extends through a fastener head along an axis towards an outlet port defined by a fastener shank.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

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 blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.

Abstract: A blade outer air seal according to an example of the present disclosure includes a seal body extending circumferentially about an axis and including at least one channel having a substantially solid radially outer surface. A substrate is radially inward of the at least one channel with respect to the axis. The substrate and the at least one channel form at least one cavity. A rotor rub strip is radially inward of the substrate.

Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.