Abstract: An eductor assembly comprises a primary nozzle configured to discharge turbine exhaust gas therefrom. The eductor assembly further comprises a cooler plenum having an inlet and an outlet and a surge plenum at least partially surrounding the cooler plenum and the nozzle, the surge plenum for conducting a surge flow. Cooling air flows through a vent between the cooler plenum and the surge plenum when there is no surge flow.

Abstract: An eductor assembly comprises a primary nozzle configured to discharge turbine exhaust gas therefrom. The eductor assembly further comprises a cooler plenum having an inlet and an outlet and a surge plenum at least partially surrounding the cooler plenum and the nozzle, the surge plenum for conducting a surge flow. Cooling air flows through a vent between the cooler plenum and the surge plenum when there is no surge flow.

Abstract: The present invention provides a method and apparatus for preventing rotation of a fastener, such as a nut, bolt or plug, to ensure that a threaded connection remains tightened. An anti-rotation spring clip includes a first arm and a second arm integrally connected by an expansion portion. An aperture in the second arm may hover around a fastener, such as a polygonal threaded fastener, and the first arm may have prongs for clamping around the outer surface of a tubular member. The anti-rotation spring clip is reusable and removable, has a long service life, and does not require special tools or permanent deformation for installation or use.

Abstract: A variable geometry vane for use in a turbine engine. The vane can be radially mounted in a shroud ring while outside the turbine engine. The shroud and vane assembly can then be mounted to an engine hub without disassembly of the shroud, eliminating the need for a split ring shroud. Once located surrounding the hub, vanes are slid radially inward until a radially inward vane button engages a hole within the hub. Vanes are locked in place using clips slid into slots within the shroud. The clips are retained in place using an adjacent engine part bolted to the face of the shroud. Once in place within the engine, vanes are attached to a control arm for airflow adjustment.

Abstract: A variable geometry vane for use in a turbine engine. The vane can be radially mounted in a shroud ring while outside the turbine engine. The shroud and vane assembly can then be mounted to an engine hub without disassembly of the shroud, eliminating the need for a split ring shroud. Once located surrounding the hub, vanes are slid radially inward until a radially inward vane button engages a hole within the hub. Vanes are locked in place using clips slid into slots within the shroud. The clips are retained in place using an adjacent engine part bolted to the face of the shroud. Once in place within the engine, vanes are attached to a control arm for airflow adjustment.