Abstract: A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a space therebetween. Spiral spacers in the space provide distributed passages through which heated lubricating oil flows. A system for separating entrained air from the lubricating oil as part of this mechanism is disclosed.

Abstract: A two fluid thermal storage device that may allow for independent heating and cooling includes a plurality of plate members with a set of dividers brazed between two of them. The set of dividers, which may define a series of passageways therein, may include a first sub-series of alternate passageways filled with a phase change material, and a second sub-series of remaining passageways that transports a fluid, the remaining passageways alternating between transporting a cooling fluid through a first fluid circuit and transporting a heating fluid through a second and independent fluid circuit. The remaining passageways that transport the cooling fluid through the first fluid circuit are defined by a first subset of dividers and the remaining passageways that transport the heating fluid through the second fluid circuit are defined by a second subset of dividers.

Abstract: A two fluid thermal storage device that may allow for independent heating and cooling includes a plurality of plate members with a set of dividers brazed between two of them. The set of dividers, which may define a series of passageways therein, may include a first sub-series of alternate passageways filled with a phase change material, and a second sub-series of remaining passageways that transports a fluid, the remaining passageways alternating between transporting a cooling fluid through a first fluid circuit and transporting a heating fluid through a second and independent fluid circuit. The remaining passageways that transport the cooling fluid through the first fluid circuit are defined by a first subset of dividers and the remaining passageways that transport the heating fluid through the second fluid circuit are defined by a second subset of dividers.

Abstract: An environmental control system (ECS) for an aircraft may be employed to regulate temperature of air entering a cabin of the aircraft. During conditioning of the air, condensate may form in the air. A multiple-stage condensate extraction unit may be incorporated into the ECS to remove the condensate. The extraction unit may be provided with two fluid collection stages built into a cylindrical duct. The duct may have a bend therein. One of the collection stages may be positioned on an upstream side of the bend while the second one of the stages may be positioned on a downstream side thereof. The combination of the two stages and their positioning on either side of the bend may provide a particularly compact and efficient condensate extraction unit.

Abstract: A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a space therebetween. Spiral spacers in the space provide distributed passages through which heated lubricating oil flows. A system for separating entrained air from the lubricating oil as part of this mechanism is disclosed.

Abstract: A flow diverter comprises a heat sink array in fluid communication with a turbine outlet and an inlet face of a heat exchanger, the heat sink array comprising a plurality of heat sink elements, the heat sink array being separated from the inlet face by a distance, and the heat sink array being positioned between the turbine outlet and the inlet face such that at least a portion of a fluid flowing from the turbine outlet contacts the heat sink array before the portion of the fluid contacts the heat exchanger inlet face.