Abstract: The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).

Abstract: The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).

Abstract: An engine (100) is provided with a powertrain including a heat engine (1) and an output shaft (A1), an electric motor (2), a battery (40) for supplying the electric motor (2) and a propeller propulsion system including a propeller (3) and a propeller shaft (A3), to which the propeller (3) is coupled. The powertrain includes a system of clutches (E123, E14, E23, E324) designed for different configurations to selectively drive the propeller using the heat engine without transmission of the rotation of the electric motor to the propeller; using the electric motor without transmission of the rotation of the heat engine to the propeller; using combined transmission of the rotation of the heat engine and the rotation of the electric motor to the propeller. The electric motor includes a stator and a rotor mounted for rotation about a shaft rigidly connected, or capable of being coupled, to the propeller shaft.

Abstract: The present invention relates to a process for the manufacture of a grout for concrete comprising a stage of mixing a hydraulic binder and water, characterized in that the process comprises a stage of deep freezing the water in the solid form.

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: A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft.

Abstract: The present invention relates to a process for the manufacture of a grout for concrete comprising a stage of mixing a hydraulic binder and water, characterized in that the process comprises a stage of deep freezing the water in the solid form.

Abstract: The rotors of a helicopter are directly connected with electric high-torque motors, and are powered by the latter. Energy generation and rotor drive are separate from each other. The high-torque motor of the main rotor is pivoted to the cabin canopy, so that it can be tilted together with the main rotor.

Abstract: The rotors of a helicopter are powered by electric motors. The electrical energy required for this purpose is produced by a motor-generator unit, which comprises one or more internal combustion engines. The motor-generator unit can be secured under the cabin floor. This yields a hybrid helicopter that can set the rotational frequency of the rotors within a large interval.

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: A reformer system has a reformer for converting a hydrocarbon-containing fuel to a hydrogen-gas-rich reformate gas, and an HC adsorber, which is connected to an output side of the reformer and adsorbs, as a function of temperature, hydrocarbons contained in the reformate gas, or for desorbing previously adsorbed hydrocarbons to the reformate gas. The reformer system transmits the reformate gas after passing through the HC adsorber to a consuming device.

Abstract: During periods of vehicle inactivity, a vehicle-based APU electric generating system may be coupled into a regional electric grid to send electricity into the grid. A currently-preferred APU is a solid oxide fuel cell system. When a large number of vehicles are thus equipped and connected, substantial electric buffering can be effected to the grid load. A vehicle-based APU can also function as a back-up generator to a docking facility in the event of power failure of the grid. Gaseous hydrocarbon is readily supplied by pipe in many locations as a commercial and residential heating fuel source, and a hydrocarbon reformer on the vehicle can be attached to the fuel source, enabling an APU to operate as a stationary power source indefinitely. An optional storage tank on the vehicle may be refueled with gaseous fuel, for example, while the battery is being electrically recharged by the grid.

Abstract: A NOx abatement system comprising: a first NOx adsorber (18) capable of being disposed in-line and downstream of and in fluid communication with an engine (12); a selective catalytic reduction catalyst (20) disposed in-line and downstream of and in direct fluid communication with the first NOx adsorber (18), wherein the selective catalytic reduction catalyst (20) is capable of storing ammonia; and an off-line reformer (24) disposed in selective communication with and upstream of the first NOx adsorber (18) and the selective catalytic reduction catalyst (20), wherein the reformer (24) is capable of producing a reformate comprising primarily hydrogen and carbon monoxide.

Abstract: An active system for regenerating a NOX adsorber and a particulate filter, the system comprising a fuel source, a reformer for generating hydrogen and carbon monoxide in fluid communication with the fuel source, a first valve, a second valve, and a third valve in fluid communication with the reformer, an oxidation catalyst, a NOX adsorber located downstream from the oxidation catalyst, a particulate filter located downstream from the NOX adsorber; and wherein the first valve, the second valve, and the third valve control fluid flow from the reformer to the oxidation catalyst, the NOX adsorber, and the particulate filter.

Abstract: A solid-oxide fuel cell system having a relatively large primary fuel cell sub-assembly for steady-state operation and a relatively small secondary fuel cell sub-assembly which is rapidly heatable to a threshold operating temperature to a) produce usable power in a short time period, b) cascade a hot exhaust into the primary fuel cell sub-assembly to assist in preheating thereof, and c) provide steam into the primary fuel cell sub-assembly to prevent coking of the anodes thereof. As the primary sub-assembly reaches its threshold temperature, it too begins to generate electricity and continues to self-heat and to be heated by the secondary sub-assembly. Preferably, the secondary sub-assembly continues to provide electricity in complement with the primary sub-assembly until the primary sub-assembly reaches full power, at which time the secondary sub-assembly may be shut down or switched to standby status for fuel efficiency, as desired.