A method for repairing a bucket of a piece of earthwork equipment is provided, the method being specifically applicable to the repair of electric shovel buckets.

A method for repairing a component is provided, where the component has a substrate comprising an outer surface and an inner surface and defining one or more grooves. Each groove extends at least partially along the outer surface of the substrate. The component further includes a structural coating, a bond coating, and a thermal barrier coating. The groove(s) and the structural coating define one or more channels for cooling the component. The repair method includes removing the thermal barrier and bond coatings, removing at least a portion of the structural coating in a vicinity of a damaged portion of the component, performing a repair operation on the damaged portion of the component, applying a structural coating at least in a vicinity of the repaired portion of the component, and applying a bond coating and a thermal barrier coating. Additional repair methods are also provided.

A drive-removal mechanism may include, but is not limited to: at least one rotatable member; and at least one drive-engaging member operably coupled to the at least one rotatable member, wherein the drive-removal mechanism is detached from at least one drive to be removed. A drive enclosure may include, but is not limited to: at least one drive-receiving member including at least one drive-receiving channel; and at least one drive-removal mechanism including: at least one rotatable member; and at least one drive-engaging member operably coupled to the at least one rotatable member, wherein the drive-removal mechanism is configured to at least partially remove at least one hot swappable drive from the at least one drive-receiving channel.

A bulkhead for a transport refrigeration unit (TRU) is provided. The bulkhead is configured to create optimal air flow on both a front side (e.g. the side where the condenser unit is located) and a rear side (e.g. the side where the evaporator unit is located) of the bulkhead, provide structural support for various components of the TRU, and provide a thermal barrier between the front side and the rear side. Also, the bulkhead is configured to include an access door and a service opening that allows a user to access TRU components located on the rear side of the bulkhead via the front side of the bulkhead. Further, the rear side of the bulkhead is configured to provide a removal support shelf that can be used as a resting surface or a sliding surface for removing components located on the rear side of the bulkhead out of the TRU from the front side of the TRU via the service opening by removing the access door.

Aspects of the disclosure are directed to repairing or restoring a liner associated with a combustor of an aircraft engine. The liner is at least partially stripped of at least one detail. An automated welding operation is applied to the liner. A coating of the liner on a cold side of the liner is retained on the liner during the welding operation.

An oily water separator for removing oil from oil-containing water, including a vessel, a filtration membrane unit and a discharge mechanism, the filtration membrane unit containing a filtration membrane module and a returning mechanism, the filtration membrane module for performing filtration in the state of allowing the module to be immersed into the oil-containing water, the filtration membrane module having an elongated filtration membrane with an opening portion, the opening portion of the filtration membrane being fixed to one end of the filtration membrane module, the opening portion of the filtration membrane being communicatively connected to the returning mechanism, and the returning mechanism being extended along the filtration membrane toward an end on a side opposite to an end portion having the opening portion thereof, the returning mechanism being communicatively connected with the discharge mechanism.

A surgical instrument. The surgical instrument includes an end effector that comprises a staple channel and an anvil that is movably translatable relative to the staple channel. A tool mounting portion is configured to interface with a robotic system and operably communicate with the end effector. The instrument further includes a first sensor that has an output that represents a first condition of a portion of the robotic system. A second sensor has an output that represents a position of the anvil. A third sensor has an output that represents a position of a reciprocating knife within the end effector. An externally accessible memory device communicates with the first, second and third sensors.

A surgical instrument. The surgical instrument includes an end effector that comprises a staple channel and an anvil that is movably translatable relative to the staple channel. A tool mounting portion is configured to interface with a robotic system and operably communicate with the end effector. The instrument further includes a first sensor that has an output that represents a first condition of a portion of the robotic system. A second sensor has an output that represents a position of the anvil. A third sensor has an output that represents a position of a reciprocating knife within the end effector. An externally accessible memory device communicates with the first, second and third sensors.

A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44). The fan case frame (44) further comprising a coupling arrangement (56) arranged to rotate about a roll axis (60) and to couple a fan case (36) to the fan case frame (44). A gas turbine engine stand assembly (68) comprising a fan stand (40) and a core stand (38). A method of splitting a gas turbine engine (10) and a method of reassembling a gas turbine engine (10).

A gas turbine engine fan stand including a base frame and a fan case frame coupled together at one edge by a hinge. The fan case frame is arranged to: rotate about the hinge between abutting the base frame and substantially perpendicular thereto; and tilt about a yaw axis perpendicular to the hinge and in the plane of the fan case frame. The fan case frame further including a coupling arrangement arranged to rotate about a roll axis and to couple a fan case to the fan case frame. A gas turbine engine stand assembly including a fan stand and a core stand. A method of splitting a gas turbine engine and a method of reassembling a gas turbine engine.