Abstract: A gas turbine engine (10) incorporates a fuel manifold (12) that distributes fuel to fuel injectors (14) that are mounted to a support casing (16). When a problem is encountered within the fuel injector (14), the problem injector (14) may be disconnected from the fuel manifold (12) and removed without disturbing the fuel manifold (12).

Abstract: An annular support (22) accommodates differential thermal growth between first and second support rings (24, 26). The support (22) prevents relative axial, circumferential lateral and bending movement between the rings (24, 26), while allowing uniform differential radial expansion and contraction.

Abstract: A ring gear (20) rotates circumferentially about a plain bearing (22) secured to the housing (10) of a centrifugal gas compressor. The ring gear (20) drives sector gears (18) for positioning variable guide vanes (14). A lever arm (32), actuator (36) and linkage (38, 40, 50) is provided for driving the ring gear (20).

Abstract: A gas turbine engine comprising an annular casing and a bearing housing located concentrically with the casing and in spaced relation thereto. An annular exhaust gas duct is formed between the bearing housing and the outer annular casing. The bearing housing includes a pair of concentric spaced-apart rings connected in a cantilevered manner. The outer ring is supported to the outer casing by angularly, spaced-apart, radially extending support members, and the inner ring includes a cylindrical inner surface to which a concentric bearing support member is tightly fitted therein. The concentric bearing support member includes angularly, spaced-apart, support contact means tightly engaging the inner cylindrical surface of the inner ring while the remainder of the bearing support is out of radial contact with the inner ring of the housing to allow for minimum thermal conduction, yet stressed for relief in the tightly fitting support member within the bearing support housing.