Abstract: A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.

Abstract: The invention concerns a device (1) comprising means (6A, 6B, 6n) which determine for each of the engines of the aircraft, an individual minimum flexible temperature and means (8) which determine a global minimum flexible temperature based on said individual minimum temperatures, enabling a maximum available thrust to be calculated.

Abstract: In a turbine engine hydrogen is injected into the combustor in response to a power output level of the turbine engine. In a preferred embodiment, gaseous hydrogen is always injected at low-power operations and switched off at mid-power and high-power operations.

Abstract: The invention relates to a filter of which the filtering portion is made from an inorganic material comprising grains of SiC bonded by a vitroceramic phase, to form a porous structure of which the apparent porosity is between 20 and 70%, said vitroceramic bonding phase comprising at least the following components, in molar percentage of the total oxides present in said phase: SiO2: 30% to 80% Al2O3: 5% to 45% MO: 10% to 45%, where MO is an oxide of a divalent cation or the sum of the oxides of the divalent cations present in said vitroceramic phase, M preferably being selected from Ca, Ba, Mg or Sr, said vitroceramic phase having a volume percentage of residual vitreous phase lower than 20%.

Abstract: A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.

Abstract: The invention concerns a device (1) comprising means (6A, 6B, 6n) which determine for each of the engines of the aircraft, an individual minimum flexible temperature and means (8) which determine a global minimum flexible temperature based on said individual minimum temperatures, enabling a maximum available thrust to be calculated.

Abstract: A filtering body (3), in particular for a motor vehicle internal combustion engine exhaust gas particulate filter (1), includes a plurality of filtering units (11a–11i) assembled by at least a joint (12) interposed between the filtering units (11a–11i) and configured so as to counter the passage of exhaust gases between the filtering units (11a–11i). The filtering body is characterized in that the joint (12) comprises a plurality of joint portions (12a–12e) locally adapted to optimize the attenuation of thermomechanical stresses liable to be generated in the filtering body (3).

Abstract: A method is provided for backwashing, by heating, a particulate filter to be purified of exhaust gases (G) of an internal combustion engine (M), in particular an internal combustion engine equipping a motor vehicle (V). The method includes controlling the start-up of a device for heating (1) the filter (F) when the engine (M) delivers an engine torque at a predetermined low threshold (Cbas).