An aircraft thrust reverser inner wall and method of manufacturing the same. The aircraft thrust reverser inner wall may include a face sheet, a perforated back sheet, and a core sandwiched between the face sheet and the perforated back sheet. The face sheet may have an inner face sheet surface and an outer face sheet surface, and the core may have an inner core surface, an outer core surface, and a plurality of cell walls extending therebetween. An electro-depositable material may be applied, via electrodeposition, in a substantially continuous layer over the outer core surface, the cell walls, and the outer face sheet surface, thus bonding the face sheet and core together. The perforated back sheet may be attached to the core at the outer core surface, and a conductive coating may be applied to the inner face sheet surface.

A turbocharger (1) includes compressor and turbine wheels (4, 5) and a shaft (6) that connects the compressor wheel (5) to the turbine wheel (4). The shaft (6) is supported by a thrust bearing assembly (20) that includes a pair of thrust washers (42a, 42b) mounted on the shaft (6), a hollow, cylindrical spacer (80) disposed on the shaft (6) between and abutting first faces (44) of the thrust washers (42a, 42b), and a thrust bearing (100) supported on the spacer (80) between the thrust washers (42a, 42b). One of the thrust bearing (100) or the first and second thrust washers (42a, 42b) includes a copper-alloy lining (60) where the lining (60) is provided in a first region (58a) and in a second region (58b), and the remainder of the thrust bearing (100) or the first and second thrust washers (42a, 42b) is lining free.

The present application provides slot seals for reducing leakages between adjacent components of turbomachinery. The seals may include a metallic shim and a coating overlying the metallic shim. The coating may be a metallic coating, a glass coating, an enamel coating or a ceramic coating. The coating may form an outer surface of the seal for engagement with seal slot surfaces of a seal slot of a turbomachine. The coating may be operable to conform to surface irregularities of the seal slot surfaces and remain coupled to the metallic shim at a predefined operating temperature and a predefined operating pressure to reduce leakage past the seal and thereby between the components. The coating may be configured to flow into depressions formed by the surface irregularities of the seal slot surfaces and remain coupled to the metallic shim at the predefined operating temperature and the predefined operating pressure.