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 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 fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.

A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

An airfoil of an aircraft with an ice protection system, the airfoil having a leading edge, the ice protection system comprising a first applying mechanism for applying an ice protection fluid along at least a portion of the leading edge of the airfoil, and an ice protection fluid recovering mechanism for recovering the ice protection fluid applied by the first applying mechanism, the ice protection fluid recovering mechanism being arranged downstream of the leading edge of the airfoil. The ice protection system further comprises a second applying mechanism for applying the ice protection fluid recovered by the ice protection fluid recovering mechanism on at least one area of the airfoil arranged downstream of the leading edge of the airfoil. An aircraft may comprise at least one airfoil provided with the ice protection system. A method may be used to protect the airfoil of an aircraft from ice accumulation.

An airfoil of an aircraft with an ice protection system, the airfoil having a leading edge, the ice protection system comprising a first applying mechanism for applying an ice protection fluid along at least a portion of the leading edge of the airfoil, and an ice protection fluid recovering mechanism for recovering the ice protection fluid applied by the first applying mechanism, the ice protection fluid recovering mechanism being arranged downstream of the leading edge of the airfoil. The ice protection system further comprises a second applying mechanism for applying the ice protection fluid recovered by the ice protection fluid recovering mechanism on at least one area of the airfoil arranged downstream of the leading edge of the airfoil. An aircraft may comprise at least one airfoil provided with the ice protection system. A method may be used to protect the airfoil of an aircraft from ice accumulation.

An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.

An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.

This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.