Abstract: An assembly method is provided during which a first component is arranged with a second component. The first component is secured to the second component using a fastener assembly. The fastener assembly includes a fastener element and a washer. The fastener element includes a wrenching feature. The washer has a full-hoop annular body with a cylindrical outer surface. The securing includes: mating a socket device with the fastener element and the washer, the socket device engaging the wrenching feature and the cylindrical outer surface; and rotating the fastener element about an axis using the socket device to tighten the fastener assembly and clamp the washer axially between the first component and the fastener element. The socket device centers the washer to the fastener element during the rotating.

Abstract: A centrifugal compressor, has: an impeller; and a housing including: a shroud extending between a first end and a second end; a structural member having an outer end securable to a casing of the gas turbine engine, an inner end of the structural member intersecting the rear side of the shroud; and a reinforced region at the location where the structural member and the rear side of the shroud intersect, a thickness of the reinforced region in a direction normal to the gaspath side greater than a nominal thickness of the shroud, the reinforced region defining a curved surface extending from a first location on the structural member to a second location on the rear side of the shroud, a portion of the curved surface having a radius that increases from a first radius to a second radius at the second location.

Abstract: A frequency tuning rib is provided on an impeller shroud to alter a natural frequency of the shroud so as to avoid coincidence with the aerodynamic excitation frequencies to which the shroud is exposed during engine operation.

Abstract: A frequency tuning rib is provided on an impeller shroud to alter a natural frequency of the shroud so as to avoid coincidence with the aerodynamic excitation frequencies to which the shroud is exposed during engine operation.

Abstract: A rotary assembly for an aircraft engine is disclosed. A shaft is mounted for rotation about a central axis and a rotary part is mounted on the shaft for common rotation therewith. The rotary part has an axial end portion extending away from a center of mass of the rotary part, the axial end portion having a radial thickness smaller than that of the rotary part at an axial location aligned with the center of mass. The shaft and the rotary part have an interface defining an interference fit between the shaft and the axial end portion of the rotary part. The interface is located at a distance along the central axis from the center of mass. An undercut is defined in the rotary part. The undercut extends axially from adjacent the interface towards the center of mass.

Abstract: A shroud configured to be disposed around an impeller of a centrifugal compressor, the shroud has a wall extending circumferentially around a central axis, the wall having an inner face oriented toward a gaspath and an outer face opposed to the inner face, a bleed slot defined in the wall and extending along at least a portion of a circumference thereof, the bleed slot defining a bleed direction from the inner face and away from the gaspath, the bleed direction at the inner face of the wall being either parallel to the central axis or oriented toward the central axis. A method of manufacturing a shroud is provided.

Abstract: A centrifugal compressor, has: an impeller; and a housing including: a shroud extending between a first end and a second end; a structural member having an outer end securable to a casing of the gas turbine engine, an inner end of the structural member intersecting the rear side of the shroud; and a reinforced region at the location where the structural member and the rear side of the shroud intersect, a thickness of the reinforced region in a direction normal to the gaspath side greater than a nominal thickness of the shroud, the reinforced region defining a curved surface extending from a first location on the structural member to a second location on the rear side of the shroud, a portion of the curved surface having a radius that increases from a first radius to a second radius at the second location.

Abstract: A rotary assembly for an aircraft engine is disclosed. A shaft is mounted for rotation about a central axis and a rotary part is mounted on the shaft for common rotation therewith. The rotary part has an axial end portion extending away from a center of mass of the rotary part, the axial end portion having a radial thickness smaller than that of the rotary part at an axial location aligned with the center of mass. The shaft and the rotary part have an interface defining an interference fit between the shaft and the axial end portion of the rotary part. The interface is located at a distance along the central axis from the center of mass. An undercut is defined in the rotary part. The undercut extends axially from adjacent the interface towards the center of mass.

Abstract: A shroud configured to be disposed around an impeller of a centrifugal compressor, the shroud has a wall extending circumferentially around a central axis, the wall having an inner face oriented toward a gaspath and an outer face opposed to the inner face, a bleed slot defined in the wall and extending along at least a portion of a circumference thereof, the bleed slot defining a bleed direction from the inner face and away from the gaspath, the bleed direction at the inner face of the wall being either parallel to the central axis or oriented toward the central axis. A method of manufacturing a shroud is provided.

Abstract: A balancing weight is disclosed. The balancing weight is engageable in a hole defined in a rotor, the hole having a predetermined cross-sectional dimension. The balancing weight comprises: a head having a predetermined weight, and a shank extending axially from the head. The shank includes at least two portions expandable in a direction transverse to a hole engagement direction between a first position in which a cross-sectional dimension of the shank is less than the predetermined cross-sectional dimension of the hole and a second position in which the cross-sectional dimension of the shank is greater than the predetermined cross-sectional dimension of the hole in the rotor. A method for installing a balancing weight to an engine rotor is also disclosed.

Abstract: A gas turbine engine for an aircraft includes a compressor section where at least one of the airfoil members defines a vane exit vector extending tangentially from a curved surface of the airfoil member adjacent a trailing edge of the airfoil member, a projection of the vane exit vector in a longitudinal plane perpendicular to a radial direction of the engine extending at an airfoil angle from the longitudinal axis. A bleed slot defined through the casing wall and providing fluid communication between the core air passage and the bleed duct extends along a slot axis. A projection of the slot axis in the longitudinal plane extends at a slot angle with respect to the longitudinal axis. The slot angle is different from the airfoil angle. A method of forming bleed slots in a gas turbine engine is also discussed.

Abstract: A cylindrical seal apparatus according to one embodiment includes a split spring ring and a split seal ring supported in a groove for example defined in a piston. The split spring ring in a tensioning condition presses against a tapered annular inner surface of the split seal ring to create a radial pre-load and an axial pre-load to the slit seal ring to establish a primary sealing contact between the seal ring and a cylinder, and a second sealing condition between the seal ring and a lower-pressure side of the groove, before the working fluid pressure is built up.

Abstract: A cylindrical seal apparatus according to one embodiment includes a split spring ring and a split seal ring supported in a groove for example defined in a piston. The split spring ring in a tensioning condition presses against a tapered annular inner surface of the split seal ring to create a radial pre-load and an axial pre-load to the slit seal ring to establish a primary sealing contact between the seal ring and a cylinder, and a second sealing condition between the seal ring and a lower-pressure side of the groove, before the working fluid pressure is built up.

Abstract: A flow regulating device in a fluid system according to one embodiment may include a housing defining a cavity receiving an orifice body. The orifice body defines a bore extending axially therethrough and includes a flexible end section, with axial slits in one example, to allow the end section to be radially compressed to change a cross-section of a flow passageway when the bore of the orifice body is included in the flow passageway.