Abstract: Apparatus, e.g., including a pump or rotary device, having a discharge casing and a discharge casing insert. The discharge casing may be configured with a discharge flow pathway for providing a flow of effluent being pumped and discharged, the discharge flow pathway having a discharge flow pathway wall, the discharge casing also configured with a discharge casing insert borehole that passes from an outer surface of the discharge casing through the discharge flow pathway wall. The discharge casing insert may include a discharge casing Venturi plug portion to be received in the discharge casing insert borehole and arranged in the discharge flow pathway, the discharge casing Venturi plug portion configured with a restricted discharge flow pathway for providing a partial obstruction in the discharge flow pathway and the flow of the effluent being pumped and discharged.

Abstract: Apparatus, e.g., including a pump or rotary device, having a discharge casing and a discharge casing insert. The discharge casing may be configured with a discharge flow pathway for providing a flow of effluent being pumped and discharged, the discharge flow pathway having a discharge flow pathway wall, the discharge casing also configured with a discharge casing insert borehole that passes from an outer surface of the discharge casing through the discharge flow pathway wall. The discharge casing insert may include a discharge casing Venturi plug portion to be received in the discharge casing insert borehole and arranged in the discharge flow pathway, the discharge casing Venturi plug portion configured with a restricted discharge flow pathway for providing a partial obstruction in the discharge flow pathway and the flow of the effluent being pumped and discharged.

Abstract: An integrated thermal protection system (TPS) for a spacecraft includes a grid that is bonded to skin of the spacecraft, e.g., to support the structural loads of the spacecraft. A plurality of thermally insulative, relatively large panels are positioned on the grid to cover the skin of the spacecraft to which the grid has been bonded. Each panel includes a rounded front edge and a front flange depending downwardly from the front edge. Also, each panel includes a rear edge formed with a rounded socket for receiving the rounded front edge of another panel therein, and a respective rear flange depends downwardly from each rear edge. Pins are formed on the front flanges, and pin receptacles are formed on the rear flanges, such that the pins of a panel mechanically interlock with the receptacles of the immediately forward panel. To reduce the transfer to the skin of heat which happens to leak through the panels to the grid, the grid includes stringers that are chair-shaped in cross-section.