Abstract: An aircraft conditioning system including: a fuel inlet (2) to a fuel conduit (3), an engine (4), a first heat exchanger (6) connected to a power unit outlet (5) of the engine, a first portion (3.1) of the fuel conduit (3) connecting the fuel inlet (2) to a fuel inlet (6.3) of the first heat exchanger (6) and a second portion (3.2) connecting a fuel outlet (6.4) of the first heat exchanger (6) to an inlet (4.1) of the engine (4), a heater (7) converting liquid fuel in the fuel conduit (3) to a low temperature gas form, a bypass conduit (8) connecting the first and second portions (3.1, 3.2) wherein the first heat exchanger (6) transfers heat from exhaust gases of the power unit outlet (5) to fuel of the fuel conduit (3).

Abstract: A heat exchanger configured to be positioned in a tail cone section of a fuselage of an aircraft and including a liner through which passes hot gases from an auxiliary power unit (APU) and plates within the liner, wherein the plates are hollow and receive a second fluid from a first collector and discharge the second fluid from the plates to a second collector.

Abstract: A conditioning system for an aircraft having a pressure accumulator connected to the heat recovery circuit and to the fuel conduct. A fluid of the fuel conduct is hydrogen (H2), or the working fluid of the heat recovery circuit comprises Nitrogen (N2), Helium (He), ethylene glycol water (EGW), and mixtures thereof, or both. Also an aircraft comprising such a conditioning system.

Abstract: An aircraft conditioning system including a fuel tank, including an outlet connected to an Auxiliary Power Unit (APU) fuel inlet, configured to maintain a pressurized gas fuel, a pressure regulator, downstream of the fuel tank, configured to regulate a pressure of the pressurized gas fuel injected to the APU inlet, a first temperature sensor downstream of the pressure regulator and a second temperature sensor upstream of an engine, a first pressure sensor inside the fuel tank, a second pressure sensor downstream of the pressure regulator and a third pressure sensor at an engine inlet, and a controller connected to the pressure sensors and the temperature sensors, the controller receiving temperature and pressure values from the pressure sensors and from the temperature sensors and actuating on at least one of the pressure regulator or the injection position of the pressurized gas fuel inside a plurality of engine combustion chambers.

Abstract: A conditioning system for an aircraft including a fuel conduit which receives a liquid fuel, an evaporator and a heater which heat the liquid fuel to convert the fuel to a gas fuel supplied to an engine on the aircraft, the evaporator transfers heat from a hot working fluid to the liquid fuel and the heater converts energy into heat applied to the liquid fuel, and a heat recovery circuit which circulates the working fluid through the evaporator and a heat exchanger in a hot exhaust gas stream generated by the engine.

Abstract: An aircraft including a combustion engine with a combustion chamber an injection device for injecting fuel in the combustion chamber and an air separation device adapted to separate air into an oxygen-enriched gas mix and an nitrogen-enriched gas mix, wherein the oxygen-enriched gas mix is injected into the combustion chamber with the fuel while the nitrogen-enriched gas mix is used to inert at least some portions of the aircraft in the environment of said combustion engine.

Abstract: A valve for a hydraulic circuit for an aircraft, the valve being configured to unite or separate multiple circuit portions in at least two configurations. More particularly, the valve allows to create one hydraulic circuit or two independent hydraulic circuits in order to circulate a coolant in two distinct manners and thus to adapt the function of the hydraulic circuit to any of two distinct phases of the functioning of an engine of the aircraft.

Abstract: An aircraft including a combustion engine with a combustion chamber an injection device for injecting fuel in the combustion chamber and an air separation device adapted to separate air into an oxygen-enriched gas mix and an nitrogen-enriched gas mix, wherein the oxygen-enriched gas mix is injected into the combustion chamber with the fuel while the nitrogen-enriched gas mix is used to inert at least some portions of the aircraft in the environment of said combustion engine.