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: 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 relates to turbine engines used in aeronautics, but also for industrial and marine turbine engines. To reduce turbine engine combustor gaseous emissions at given combustor sizes or to reduce combustor sizes at given combustor gaseous emissions, the invention proposes the injection of hydrogen into the combustor in response to a power output level. According to 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 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.