Abstract: A system for shielding an interior metal surface of a metal container from a hot fluid within the metal container wherein the hot fluid is at a temperature greater than a temperature limit of the metal, including a first insulating layer including metal clad insulation proximate the interior metal surface, a second insulating layer spaced from the first insulating layer including a perforated reflective metal shield and a third insulating layer spaced from the second insulating layer which is structurally stable and substantially inert to the hot fluid.

Abstract: A closed-loop Brayton cycle (topping system) takes in heat energy at very high temperatures and rejects heat energy as input heat energy to a closed-loop Rankine cycle (base system). Heat energy input to the base system comes partially or solely from the high-temperature topping system. Materials having high strength at high temperatures enable the topping system to extract significant mechanical energy from thermal energy contained in high temperature working fluid and discharge waste energy from the topping system to the base system at temperatures sufficiently high to be fully useable input to the base system. In the preferred embodiment, closed-loop Brayton-cycle operates at maximum temperatures greatly in excess of maximum temperatures of a conventional steam Rankine-cycle. Consequently, a high-temperature closed-loop Brayton cycle topping system of significant output and efficiency can act as an addition to a conventional steam power-generating station.

Abstract: A thrusting nozzle (24) comprises an annular shell (34) and an inner body (30). The contours of the inner wall (42) of the shell (34) and the outer wall (44) of the inner body (30) form a convergence zone (48), a throat (50), and an outlet zone (52) in sequence from the nozzle inlet (54) to the nozzle outlet (56). The inner body (30) extends from the upstream end of the nozzle to a point downstream of the throat (50). In the convergence zone (48), the cross section area of the flow passage continuously and gradually decreases from the nozzle inlet (54) to the throat (50). In the outlet zone (52), the cross section area of the flow passage can gradually increase from the throat (50) to the nozzle outlet (56). The nozzle (24) can be mounted as part of a jet engine (10), with the nozzle inlet (54) being connected directly to the discharge of a gas turbine (22).

Abstract: An air-cooled contoured plug fitted within the engine tailpipe to physica block any direct view to the turbine section. A vortex cavity is provided around the plug just aft of the plug maximum diameter in order to reduce the length of the cone-shaped plug. The trapped vortex reenergizes the boundary layer built up along the cone surface and allows the flow of hot gases to turn the corner without separating.