Abstract: A clearance control assembly for providing clearance control between a blade outer air seal and an airfoil tip of a gas turbine engine includes an outer case, a first blade outer air seal carrier, a blade outer air seal, an actuator, a load-applying member, and a lever. The first blade outer air seal carrier is positioned radially inward of the outer case. The blade outer air seal is positioned radially inward of and mounted to the blade outer air seal carrier. The load-applying member is positioned to be acted upon by the actuator during operation of the actuator. The lever is connected to the case and is operably in contact with the load-applying member and the first blade outer air seal carrier.

Abstract: Thermal lifting members for blade outer air seal supports of gas turbine engines include a hollow body defining a thermal cavity therein, at least one inlet fluid connector fluidly connected to the thermal cavity configured to supply hot fluid to the thermal cavity from a fluid source, at least one outlet fluid connector fluidly connected to the thermal cavity configured to allow the hot fluid to exit the thermal cavity, and at least one lifting hook configured to engage with a blade outer air seal support, wherein the thermal lifting member is configured to thermally expand outward when hot fluid is passed through the thermal cavity such that during thermal expansion the at least one lifting hook forces the blade outer air seal support to move outward.

Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.

Abstract: A rotor assembly for a gas turbine engine includes a rotor disk. The rotor disk includes a heat barrier feature radially inward of a rotor blade and radially outward of a rotor disk.

Abstract: A gas turbine engine rotor assembly includes a rotor disk with a slot. A rotor blade has a root supported within the slot. A heat shield is arranged in a cavity in the slot between the root and the rotor disk. An axial retention feature is configured to axially maintain the heat shield within the slot.

Abstract: A shaft coupling between a first shaft and a second shaft includes a seal assembly to minimize leakage. The seal assembly includes a ring press fit against an inner surface of the first shaft and a clearance fit with an inner surface of the second shaft. A seal is supported between the ring and the inner surface of the second shaft.

Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

Abstract: An apparatus includes a body, a driver, a plurality of shafts, and a plurality of arms. The body is configured for insertion into a component and the driver is adapted for movement relative to the body. The plurality of shafts extend through the body and are connected to the plurality of arms. The tool is configured such that contact by the driver against the shaft rotates the plurality of shafts to pivot the plurality of arms.

Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.

Abstract: An apparatus includes a body, a driver, a plurality of shafts, and a plurality of arms. The body is configured for insertion into a component and the driver is adapted for movement relative to the body. The plurality of shafts extend through the body and are connected to the plurality of arms. The tool is configured such that contact by the driver against the shaft rotates the plurality of shafts to pivot the plurality of arms.

Abstract: A lock assembly includes a lock body with an undercut slot which receives a retaining wire of a polygon shape.

Abstract: An apparatus includes a body, a driver, a plurality of shafts, and a plurality of arms. The body is configured for insertion into a component and the driver is adapted for movement relative to the body. The plurality of shafts extend through the body and are connected to the plurality of arms. The tool is configured such that contact by the driver against the shaft rotates the plurality of shafts to pivot the plurality of arms.

Abstract: An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.

Abstract: A gas turbine engine includes a disk having an annular hub circumscribed about a centerline with an annular web extending radially outward from the hub to an annular rim. A multiple of slots extend generally axially through the rim and at least one of the multiple of slots having an asymmetric slot root for lower stress and higher service life.

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk with a circumferentially intermittent slot structure that extends radially outward relative to an axis of rotation. A heat shield has a multiple of radial tabs engageable with the circumferentially intermittent slot structure to provide axial retention of the cover plate to the rotor disk.

Abstract: An apparatus includes a body, a driver, a plurality of shafts, and a plurality of arms. The body is configured for insertion into a component and the driver is adapted for movement relative to the body. The plurality of shafts extend through the body and are connected to the plurality of arms. The tool is configured such that contact by the driver against the shaft rotates the plurality of shafts to pivot the plurality of arms.

Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.

Abstract: A lock assembly includes a lock body with an undercut slot which receives a retaining wire of a polygon shape.

Abstract: An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk with a circumferentially intermittent slot structure that extends radially outward relative to an axis of rotation. A heat shield has a multiple of radial tabs engageable with the circumferentially intermittent slot structure to provide axial retention of the cover plate to the rotor disk.