A method of separating a gas turbine engine includes steps to support the gas turbine engine on a core stand, and to move a fan stand into axial alignment with a core stand. The fan stand includes a base frame and a fan case frame coupled to the base frame at one edge by a hinge. The fan case frame rotates about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and includes a coupling arrangement that couples a fan case to the fan case frame. The method further includes steps to rotate and tilt the fan case frame into abutting relation with the fan case, couple the fan case to the fan case frame, decouple the fan case and core engine, and translate at least part of the core stand axially to separate the gas turbine engine.

An acoustic panel (200) for an aircraft nacelle (100) may comprise a perforated first skin (220), a second skin (230), and a core (210) sandwiched between them. A damaged portion of the perforated first skin may be removed. A fiberglass ply (510) may be coupled to the acoustic panel. A pressure differential may cause the fiberglass ply to form dimples (515) within the perforations (325) of the first skin. The fiberglass ply may be used as a template to drill holes in a replacement patch (400).

A rotorcraft service fixture includes a fixture body and one or more rotor assembly connectors rigidly attached to or integral with the fixture body. The one or more rotor assembly connectors are sized and shaped to provide an interference fit with a portion of a rotor assembly of a rotorcraft to removably attach the fixture body to the portion of the rotor assembly. The rotorcraft service fixture also includes one or more support connectors rigidly attached to or integral with the fixture body. The one or more support connectors are sized and shaped to provide an interference fit with a partially detached component of the rotor assembly to immobilize the partially detached component during inspection or maintenance of the rotor assembly.

A viscous clutch head may be replaced by selecting a viscous clutch head and a mount adapter. The viscous clutch head and the mount adapter may be selected from a group of universal modular fan drives and from a group of mount adapters. The mount adapter of a threaded type or a flange and bolt type may be selected. Depending on the viscous clutch head to be replaced, a fan adapter and/or a pilot adapter may also be selected from a group of fan adapters and from a group of pilot adapters. Accordingly, a range of models of viscous fan clutch systems may be replaced by using a limited number of parts. These parts may be stored on a tool cart. As different models of viscous fan clutch systems may be replaced using a limited number of parts, the in-stock inventory of replacement parts may be reduced.

A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.

A coolable wall element for a gas turbine, having a base body with a first surface subjectable to a hot gas, second surface arranged opposite of the first surface, and first seat for housing edges of an impingement plate. The wall element has an impingement plate partly inserted into the first seat located at a distance and adjacent to the second surface. A coolable wall element with extended life time is provided with the impingement plate which is removably attached to the base body having a snap-in connection with a bendable retention tab extending from the rest of the impingement plate to a free end of the retention tab, wherein the base body has a second seat for the free end of said tab, the second seat blocks the moving of the impingement plate relative to the main body when the bendable retention tab is released.

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.

An acoustic panel (200) for an aircraft nacelle (100) may comprise a perforated first skin (220), a second skin (230), and a core (210) sandwiched between them. A damaged portion of the perforated first skin may be removed. A fiberglass ply (510) may be coupled to the acoustic panel. A pressure differential may cause the fiberglass ply to form dimples (515) within the perforations (325) of the first skin. The fiberglass ply may be used as a template to drill holes in a replacement patch (400).

A rotor lock assembly for locking a rotor of a wind turbine. The rotor lock assembly has at least one relocatable rotor lock. The relocatable rotor lock has a housing, a bushing element, a pin shaft position within the bushing element, and a locking mechanism. The housing includes a mounting portion adapted for mounting to a bearing housing adjacent to a rotor lock plate of the rotor.

A method of repairing a diaphragm of a rotary machine includes removing an initial steam path from the diaphragm. The initial steam path includes a plurality of initial partitions. Each initial partition is associated with an original trailing edge profile and an original axial length. The method also includes coupling a replacement steam path to the diaphragm. The replacement steam path includes a plurality of replacement partitions. Each replacement partition has a replacement axial length that is greater than the original axial length.