Abstract: In a preferred embodiment, a log-type intake manifold for a diesel engine has a longitudinal passage with four equally spaced lateral outlet openings on one side and a centrally disposed inlet opening on the other side of the passage. Similar outlet flow conditions are created in the outlet passages by the addition of at least one flow directing vane at an outlet toward one end of the passage from the inlet to redirect the outlet gas flow into a pattern similar to that of the naturally occurring gas flow patterns at the outlet openings located toward the other end of the passage from the inlet.

Abstract: A generally cup-shaped fuel slinger concentrically secured by its base portion to a rotatable shaft located in a combustion chamber and having a radially inwardly extending lip at its open end provided with a plurality of circumferentially spaced notches opening toward the shaft and spaced at their bottommost portion from the inner annular surface of the slinger side wall. Fuel is delivered by a single tube through the open end of the slinger and is centrifuged outwardly against the inner annular surface of the slinger side wall, and thereafter delivered from the slinger to the combustion chamber through the notches. The slinger is located between a radial turbine and a compressor of a gas turbine engine. The fuel supply tube projects axially through a vane in the diffuser, radially along the diffuser, and then axially into the fuel slinger between the lip and the outer periphery of the adjacent shaft portion. In the disclosed embodiment the notches are generally V-shaped.

Abstract: A single shaft gas turbine engine of the type having a shaft assembly including, in axial alignment, a radial turbine element, a central slinger ring element, a radial compressor element, and a geared power takeoff element. The elements of the shaft assembly are interconnected by a tie bolt. An annular combustor liner defines a combustion chamber that encircles the central slinger ring. The shaft assembly is journaled by two bearings which are respectively located outboard of the turbine and on the geared power takeoff element. Each bearing is carried by a tubular support. Each tubular support has a free end carrying the respective bearing and another end secured to the bearing. The ends are spaced and interconnected by circumferentially spaced ribs to provide a flexible support for the prospective bearing. The gear on the power takeoff element drives a larger gear to withdraw power from the engine.