In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.

Cooled cooling air system for a gas turbine

An air conditioning system that includes desiccant compartments for holding a desiccant; a heat exchanger, a blower and a vessel. The heat exchanger can be filled with a heat transfer medium, while the blower blows ambient air by the heat exchanger such that the blown air is cooled and the heat exchanger is warmed such that thermal energy increases and is transferred from the air to the heat transfer medium causing the heat transfer medium to turn into vapor. The vapor is then diffused to one of the desiccant compartments such that the vapor is adsorbed onto the desiccant creating a mixture. Then an energy source is applied to the mixture such that the vapor and desiccant are separated. The separated vapor is transported to the vessel where it is condensed and then sent back to the heat exchanger, such that the system is able to be continuously operating.

Air-conditioning system

In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid.

Return fluid air cooler system for turbine cooling with optional power extraction

An air cycle machine is provided and includes a compressor section having a variable area diffuser, a turbine section having an inlet nozzle with a variable size, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are mounted, the turbine section driving rotation of the shaft to drive the compressor section with the motor.

Motor driven cabin air compressor with variable diffuser

An onboard electrochemical system of an electrochemical cell including a cathode and an anode separated by an electrolyte separator is selectively operated in either of two modes. In a first mode of operation, water or air is directed to the anode, electric power is provided to the anode and cathode to provide a voltage difference between the anode and the cathode, and nitrogen-enriched air is directed from the cathode to an aircraft fuel tank or aircraft fire suppression system. In a second mode of operation, fuel is directed to the anode, electric power is directed from the anode and cathode to one or more aircraft electric power-consuming systems or components, and nitrogen-enriched air is directed from the cathode to a fuel tank or fire suppression system.

On-board aircraft electrochemical system

An aircraft air-conditioning unit (10) includes a compressor (18) and a motor (20) driving the compressor (18). A fuel cell system (24) is connected directly to a control unit (22) for controlling the motor (20) driving the compressor (18), wherein the control unit (22) is adapted to convert electrical energy directly generated by the fuel cell system (24) into corresponding electrical control signals for controlling the motor (20) driving the compressor (18). In a method for operating an aircraft air- conditioning unit (10), which includes a compressor (18) and a motor (20) driving the compressor (18), a control unit (22) for controlling the motor (20) driving the compressor (18), which is directly connected to a fuel cell system (24), converts electrical energy directly generated by the fuel cell system (24) into corresponding electrical control signals for controlling the motor (20) driving the compressor (18).

Aircraft air-conditioning unit and method for operating an aircraft air-conditioning unit

A fuel cell system for an aircraft includes a fuel cell, wherein at the cathode side a cathode inlet and a cathode outlet is provided, and wherein at the anode side an anode inlet and an anode outlet is provided, and a cathode recirculation channel for passing the cathode product fluid from the cathode outlet to the cathode inlet. In the fuel cell system, the water content of the cathode product fluid in the cathode recirculation channel can be reduced or at least stabilized in a possibly effective way, because the cathode recirculation channel includes a water extraction device for extracting water from the cathode product fluid.

Fuel cell system, a fire fighting system, and an aircraft

A supply system(2) for providing at least oxygen depleted air and water in a vehicle, the system (2) comprising a catalytic converter (4), at least one hydrogen supply means (6), at least one air supply means (12, 14), at least one outlet for oxygen depleted air, and a control unit (46) coupled with the catalytic converter (4) The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air

Supply system and method for providing electric energy, oxygen depleted air and water as well and aircraft having such a supply system

A fuel cell system (2) for a vehicle comprises at least one fuel cell (4), at least one fuel cell heat exchanger (10) arranged in or at the at least one fuel cell (4) for receiving heat of the at least one fuel cell (4), at least one thermal dissipation unit (26), at least one additional heat exchanger (18, 28) and a cooling loop (12) having a plurality of fluid line segments for conveying a coolant. The at least one fuel cell heat exchanger (10) is coupled with the at least one thermal dissipation unit (26) through the cooling loop (12), and the additional heat exchanger (18, 28) is arranged in the cooling loop (12) and is adapted for receiving heat from an external source and for raising the temperature of a coolant flowing in the cooling loop (12).

Improved cooling concept for a fuel cell system for a vehicle and aircraft having such a fuel cell system

A system for cooling an aircraft fuel cell system comprising a first cooling circuit thermally coupled to a first fuel cell, to remove thermal energy generated by the first fuel cell during operation from the first fuel cell, and a first heat exchanger arranged in the first cooling circuit and adapted to transfer thermal energy, removed from the first fuel cell via the first cooling circuit, to the aircraft surroundings. The system comprises a second cooling circuit thermally coupled to a second fuel cell, to remove thermal energy generated by the second fuel cell during operation from the second fuel cell, and a second heat exchanger arranged in the second cooling circuit and adapted to transfer thermal energy, removed from the second fuel cell via the second cooling circuit, to the aircraft surroundings. The first cooling circuit is thermally couplable to the second cooling circuit.

System and method for cooling an aircraft fuel cell system

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