Abstract: A labyrinth seal, has: rotating and static components rotatable relative to one another relative to a central axis, the rotating component securable to a shaft via a tight fit engagement at an engagement location on the rotating component, the static component securable to a housing; teeth protruding from one of the rotating and static components towards a seal land defined by the other one of the rotating and static components; and clearances between the teeth and the seal land, a first clearance of the clearances greater than a second clearance of the clearances, the first clearance located closer to the engagement location of the rotating component than the second clearance.

Abstract: A lock washer for preventing relative rotation between an inner component and an outer component in an aircraft engine. The lock washer comprises an annular body having an inner circumferential surface and an outer circumferential surface radially spaced apart to define a radial thickness of the annular body. Radially-inward protruding tabs extend radially inwardly from the inner circumferential surface of the annular body and are operable for engagement with slots in the inner component. Radially-outward protruding tabs extend radially outwardly from the outer circumferential surface of the annular body and are operable for engagement with slots in the outer component. The radially-outward protruding tabs are circumferentially offset from the radially-inward protruding tabs such that the radially-outward protruding tabs and the radially-inward protruding tabs are all free of circumferential overlap.

Abstract: A gas turbine engine rotor having an axis, comprising: a body about the axis having an inner surface, a seat having an outer seat edge at a first radial location surrounded by the inner surface at a second radial location, a lip along the inner surface having an inner lip edge spaced axially away from the seat to define a gap, the lip at a rated axial location between the inner lip edge and the seat facing toward the seat at a normal angle; a damper in the gap having first and second damper surfaces, the first damper surface adjacent the seat; and a split ring in the gap adjacent the second damper surface, having an outer ring edge spaced from the inner surface, engaging the lip at the rated axial location and resiliently expandable against the lip deflects the split ring to load the damper against the seat.

Abstract: A gas turbine engine rotor having an axis, comprising: a body about the axis having an inner surface, a seat having an outer seat edge at a first radial location surrounded by the inner surface at a second radial location, a lip along the inner surface having an inner lip edge spaced axially away from the seat to define a gap, the lip at a rated axial location between the inner lip edge and the seat facing toward the seat at a normal angle; a damper in the gap having first and second damper surfaces, the first damper surface adjacent the seat; and a split ring in the gap adjacent the second damper surface, having an outer ring edge spaced from the inner surface, engaging the lip at the rated axial location and resiliently expandable against the lip deflects the split ring to load the damper against the seat.

Abstract: A rotor assembly comprises a first body and a second body extending about a rotation axis. The first body has an inner surface, a seat surrounded by the inner surface, and a groove extending circumferentially into the inner surface. The second body has an outer surface surrounded by the inner surface. An annular gap is defined radially between the inner surface and the outer surface and axially between the seat and the groove. A locking washer is mounted in anti-rotational engagement with the inner surface and the outer surface relative to the rotation axis. A split ring is disposed in the annular gap. The split ring is resiliently expandable radially outwardly under centrifugal load such that expanding the split ring radially against the groove axially deflects the split ring toward the seat relative to the first body and to the second body so as to axially load the locking washer against the seat.

Abstract: A labyrinth seal assembly for a gas turbine engine having a rotatable shaft. The labyrinth seal assembly has: a housing defining a cavity for receiving a lubricant; a labyrinth seal between the housing and the rotatable shaft of the gas turbine engine, the labyrinth seal having a seal rotor securable to the rotatable shaft and a seal stator secured to the housing; and an insulation layer between the seal stator and the housing, the insulation layer composed of a material different than those used for the seal stator and the housing.

Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.

Abstract: A labyrinth seal, has: rotating and static components rotatable relative to one another relative to a central axis, the rotating component securable to a shaft via a tight fit engagement at an engagement location on the rotating component, the static component securable to a housing; teeth protruding from one of the rotating and static components towards a seal land defined by the other one of the rotating and static components; and clearances between the teeth and the seal land, a first clearance of the clearances greater than a second clearance of the clearances, the first clearance located closer to the engagement location of the rotating component than the second clearance.

Abstract: A seal and bearing assembly having a bearing received within a housing. The bearing is disposed radially outwardly of a shaft and having an inner portion and an outer portion. The outer portion has a protrusion extending at least in an axial direction. An outer diameter of the outer portion is sized to provide a radial gap between the outer diameter and the housing section. The gap receives a film of lubricant for damping movements of the bearing relative to the housing section. A sealing member has a rotating portion configured for rotation with the shaft radially spaced apart from a static portion defined by the protrusion of the bearing outer portion. There is also disclosed a method of operating such an assembly.

Abstract: A labyrinth seal assembly for a gas turbine engine having a rotatable shaft. The labyrinth seal assembly has: a housing defining a cavity for receiving a lubricant; a labyrinth seal between the housing and the rotatable shaft of the gas turbine engine, the labyrinth seal having a seal rotor securable to the rotatable shaft and a seal stator secured to the housing; and an insulation layer between the seal stator and the housing, the insulation layer composed of a material different than those used for the seal stator and the housing.

Abstract: A sealing assembly for sealing between an oil cavity and an air cavity of a gas turbine is provided. The sealing assembly comprising a seal having a seal element and a circumferential seal housing receiving the seal element. The seal housing has an annulus extending circumferentially around a center axis, radially between an outer periphery and an inner periphery, and axially along the center axis between a first surface and a second surface. The seal housing has a collecting channel defined circumferentially in the inner periphery about the center axis and a draining pocket defined in a portion of the seal housing configured and disposed to in use collect liquid oil during engine operation. The draining pocket extends from the collecting channel to the first surface and configured to communicate collected liquid oil from the collecting channel to the oil cavity.

Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.

Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.

Abstract: A sealing assembly for sealing between an oil cavity and an air cavity of a gas turbine is provided. The sealing assembly comprising a seal having a seal element and a circumferential seal housing receiving the seal element. The seal housing has an annulus extending circumferentially around a center axis, radially between an outer periphery and an inner periphery, and axially along the center axis between a first surface and a second surface. The seal housing has a collecting channel defined circumferentially in the inner periphery about the center axis and a draining pocket defined in a portion of the seal housing configured and disposed to in use collect liquid oil during engine operation. The draining pocket extends from the collecting channel to the first surface and configured to communicate collected liquid oil from the collecting channel to the oil cavity.

Abstract: A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. Pressure relief dimples are provided around the outer diameter of the ring for locally reducing contact pressure at the outer diameter below a value at which the damper ring locks in the groove by friction forces when subject to centrifugal loads.

Abstract: A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. The damper ring has a circumferentially segmented ring body having a non-uniform circumferential stiffness around its circumference including a locally reduced stiffness in a circumferential direction between each pair of circumferentially adjacent ring segments.

Abstract: There is disclosed a seal and bearing assembly having a bearing received within a housing. The bearing is disposed radially outwardly of a shaft and having an inner portion and an outer portion. The outer portion has a protrusion extending at least in an axial direction. An outer diameter of the outer portion is sized to provide a radial gap between the outer diameter and the housing section. The gap receives a film of lubricant for damping movements of the bearing relative to the housing section. A sealing member has a rotating portion configured for rotation with the shaft radially spaced apart from a static portion defined by the protrusion of the bearing outer portion. There is also disclosed a method of operating such an assembly.

Abstract: A gearbox in a gas turbine engine includes an enclosed gearbox housing, at least a pair of intermeshing gears lubricated and rotatably supported within the gearbox housing, and a baffle apparatus axially spaced apart from and positioned at least at one side of the pair of gears, the baffle apparatus including a collector defining a main opening adjacent a meshing point of the intermeshing gears for collecting and redirecting lubricant squeezed out axially from the intermeshing gears.

Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.

Abstract: A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. Pressure relief dimples are provided around the outer diameter of the ring for locally reducing contact pressure at the outer diameter below a value at which the damper ring locks in the groove by friction forces when subject to centrifugal loads.