Abstract: A radial inflow particle separator includes a pair of axially and radially spaced curvilinear walls cooperatively defining a circumferential flow path leading radially inwardly and axially to an engine. Preferably, the particle separator is employed with a turbine engine which is operated at times in an environment laden with dust and particulate matter. Such an environment is typically encountered by a turbine engine of a helicopter, or off-road vehicle. The particle separator provides dust and particulate control features including aero-inertial, particle trajectory, particle boundary-rebound, and scavenge flow tailoring to achieve a dust and particulate separation efficiency as good as or better than the best conventional axial-flow particle separators. This particle separation effectiveness is achieved in a radial inflow particle separator which is smaller and lighter in weight than axial flow devices, and which packages advantageously with the essential structures of a turbine engine.

Abstract: A method and apparatus for varying the effective area of a jet engine exhaust nozzle. The apparatus includes a center body disposed upstream of the nozzle throat and configured to form a recirculation wake extending to and through the nozzle throat. The conditions of fluid flow are selectively variable, for example, by axial movement of a portion of the center body, to vary that portion of the nozzle throat which is effectively blocked by the recirculation wake so as to be unavailable for downstream motive fluid flow.