A bleed system including control circuitry and a variable jet pump. The control circuitry is configured to receive a signal indicative of a fluid parameter in the bleed system and cause the jet pump to alter a mixing ratio of a higher pressure gas and a lower pressure gas based on the signal. The jet pump is configured to combine the lower pressure gas and the higher pressure gas in the mixing ratio to generate a mixed gas. The jet pump is configured to supply the mixed gas to one or more gas loads in the bleed system. In examples, the control circuitry is configured to establish a system setpoint for the fluid parameter based on an operating status of the one or more gas loads.

Vehicles, environmental control systems, and methods for operating an environmental control system are provided. In one example, the environmental control system (ECS) includes an ECS refrigeration unit that is configured to receive ambient air and a first portion and a second portion of hot bleed air. The ECS refrigeration unit is operable to indirectly exchange heat between the first portion of the hot bleed air and the ambient air to form a partially cooled, hot air stream, and to compress, further indirect heat exchange, and expand the partially cooled, hot air stream to form a cooled and expanded air stream. A low limit valve control regulates a low limit valve to control a rate of introduction of the second portion of the hot bleed air to the cooled and expanded air stream to form a combined air stream that when exiting the ECS refrigeration unit is a sub-freezing air stream.

An air-liquid heat exchanger assembly for an environmental control system of an aircraft includes a heat exchanger, a controller, and a bypass valve. The heat exchanger includes a first chamber and a second chamber. The first chamber has a first inlet that is provided a liquid and a first end that is provided air. The second chamber is arranged adjacent the first chamber. The bypass valve is operably coupled to the controller. The bypass valve having an inlet coupled to a first outlet of the first chamber, a first outlet coupled to a second inlet of the second chamber, and a second outlet coupled to a bypass conduit. The controller adjusts a position of the bypass valve to control the flow of liquid through the second chamber and the bypass conduit.

An aircraft humidifier is engineered as a stand-alone, fully integrated aircraft humidifier that is suitable for providing uniform, non-wetting humidified air disbursed by the aircraft humidifier into ambient air to increase the relative humidity in low humidity environments such as aircraft interiors, including cockpits, cabins, crew rests, cargo holds, and lavatories as well as any other enclosed areas.

The invention relates to a loop (40) for extracting water from an air conditioning system of a cabin (5) of an air or rail transport vehicle comprising an air cycle turbine engine (20), the loop comprising: a condenser (41); a three-dimensional mesh grid (45) housed in an outlet box (42) of the condenser and configured to be able to capture water droplets in a stream of moist air condensed by the condenser; a water recovery unit (46) opening on the condenser outlet box (42) and arranged under the three-dimensional mesh grid (45) so as to be able to recover, by force of gravity, the water collected by the three-dimensional mesh grid (45); an air return pipe (44) linking the outlet box (42) to a supply interface for directly or indirectly supplying the turbine of the air conditioning system.

The invention relates to an aircraft incorporating an enhanced power unit for generating electric, pneumatic and/or hydraulic power for the aircraft during all stages of the aircraft operation. The power unit (1) comprises: a heat engine (14) with a drive shaft (2) and a combustion gases exhaust (7). The power unit (1) also includes a Rankine cycle system (12) for recovering thermal energy from a heat source of the power unit (1) for the assistance of the heat engine (14). The heat source for the Rankine cycle system can be taken from the exhaust gases of the heat engine, from the oil coolant circuit of the heat engine or from the output of a compressor driven by the heat engine. Preferably, the aircraft cabin air is reused as a source of oxygen for the combustion. The invention reduces bleed air extraction from the aircraft main engines thereby reducing fuel consumption.

A water extractor is provided and includes a helical channel, a toroidal body encompassing the helical channel and defining an exhaust plenum beyond the helical channel and comprising a first outlet, an outer body defining a settling chamber about the toroidal body and including a second outlet and a drain and a scupper disposed to direct moisture, which is separated from a medium flowing through the helical channel, from the helical channel and into the settling chamber. The medium is flowable from the helical channel into the exhaust plenum and then sequentially through the first and second outlets to pressurize collected moisture flow from the settling chamber and through the drain.

A bleed system including control circuitry and a variable jet pump. The control circuitry is configured to receive a signal indicative of a fluid parameter in the bleed system and cause the jet pump to alter a mixing ratio of a higher pressure gas and a lower pressure gas based on the signal. The jet pump is configured to combine the lower pressure gas and the higher pressure gas in the mixing ratio to generate a mixed gas. The jet pump is configured to supply the mixed gas to one or more gas loads in the bleed system. In examples, the control circuitry is configured to establish a system setpoint for the fluid parameter based on an operating status of the one or more gas loads.

A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a water separator configured to receive the compressed air from the compressor and remove moisture from the compressed air to dry the compressed air. Furthermore, the system includes a turbine configured to receive the dried air from the heat exchanger, with the dried air expanding as the dried air flows through the turbine. Moreover, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, the moisture removed from the compressed air by the water separator is routed to the defroster to melt the captured frozen particulate matter.

A mixing device that is particularly suitable for use in an aircraft air-conditioning system comprising a cold air supply line adapted to supply cold air to the mixing device. A first recirculation air supply line is adapted to supply recirculation air to the mixing device. A mixing chamber is connected to the cold air supply line and the first recirculation air supply line and is adapted to supply the cold air supplied to the mixing device via the cold air supply line with the recirculation air supplied to the mixing device via the first recirculation air supply line. The first recirculation air supply line has a heat transfer portion which is thermoconductively connected to an area of a wall delimiting the mixing chamber that is at risk of icing.